CN111810454A - Casing, compressor and stability expanding method based on self-circulation oscillation jet flow - Google Patents
Casing, compressor and stability expanding method based on self-circulation oscillation jet flow Download PDFInfo
- Publication number
- CN111810454A CN111810454A CN202010699826.7A CN202010699826A CN111810454A CN 111810454 A CN111810454 A CN 111810454A CN 202010699826 A CN202010699826 A CN 202010699826A CN 111810454 A CN111810454 A CN 111810454A
- Authority
- CN
- China
- Prior art keywords
- outlet
- flow
- feedback
- bleed air
- channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000010355 oscillation Effects 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title claims abstract description 10
- 239000012530 fluid Substances 0.000 claims abstract description 28
- 238000004891 communication Methods 0.000 claims description 2
- 230000000087 stabilizing effect Effects 0.000 claims description 2
- 238000000926 separation method Methods 0.000 abstract description 19
- 230000000694 effects Effects 0.000 abstract description 16
- 230000002829 reductive effect Effects 0.000 abstract description 14
- 230000009471 action Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000000411 inducer Substances 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/002—Details, component parts, or accessories especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a casing, a gas compressor and a stability expanding method based on self-circulation oscillation jet flow.A fluid oscillator flow channel is arranged in the casing, and gas flow enters the fluid oscillator flow channel from an oscillation jet flow bleed air inlet between an n + m-stage stator or a rotor of the casing; the pressure of the oscillation jet flow bleed air inlet is greater than that of the oscillation jet flow outlet between the nth stage stator or the nth stage rotor, and after the airflow passes through the flow channel of the fluid oscillator, oscillation jet flow is formed at the oscillation jet flow outlet between the stators, so that the corner area flow separation and the suction surface flow separation corresponding to the top ends of the stator blade grids are reduced; or an oscillating jet is formed at an oscillating jet outlet of the rotor, so that secondary flow of a blade top gap of a corresponding rotor blade is reduced, and the stable working margin of the gas compressor is improved; due to pressure difference, when the oscillation jet flow bleed air inlet is positioned between the nth + m-stage stator or rotor, the flow channel of the fluid oscillator generates a suction effect on the boundary layer at the top end of the nth + m-stage stator or rotor and secondary flow, so that the flow separation of the n + m-stage stator or rotor is reduced; the stability expanding effect is generated.
Description
Technical Field
The disclosure relates to casing treatment of a gas compressor, in particular to a casing based on self-circulation oscillation jet flow, a gas compressor and a stability expanding method thereof
Background
The main inducers of the stalling of the compressor generally comprise flow separation of a blade surface, complex vortex system action of an end wall and a corner region and the like, and the stability and the efficiency of the compressor can be improved by inhibiting the flow separation of the blade surface, leakage flow and secondary flow of a blade tip and reducing the flow blockage degree of an end region by a passive or active flow control method, so that the overall performance of the compressor is improved, and the stable working range and the stable working efficiency of the compressor are enlarged. In the prior art, a steady-state jet flow is formed by utilizing the pressure difference between the front stage and the rear stage of a gas compressor or between the suction surface and the pressure surface of a blade, so that the flow overcomes the adverse pressure gradient, and the flow separation is reduced or eliminated. A great deal of research shows that the control efficiency of flow separation can be greatly improved by adopting unsteady state disturbance, but the working condition in an aeroengine is severe, the reliability requirement on all parts is extremely high, and the difficulty of using unsteady state flow control is lack of an exciter with simple structure and high reliability. The unsteady-state flow control exciter used in the active control research of the existing gas compressor has the defects of poor safety, low reliability, insufficient excitation strength and the like.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present disclosure provides a casing, a gas compressor and a stability expansion method thereof based on self-circulation oscillation jet, and the specific implementation manner is as follows:
a cartridge receiver based on self-circulation oscillation jet flow is provided with a fluid oscillator flow channel; the fluidic oscillator flow channel includes: the jet control system comprises an oscillating jet bleed air inlet, at least one oscillating jet outlet and two feedback channels, wherein the two feedback channels are used for feeding back part of jet which flows from the oscillating jet bleed air inlet to the oscillating jet outlet to a connecting part between the oscillating jet bleed air inlet and the oscillating jet outlet;
the oscillating jet flow bleed air inlet is arranged on the inner wall of the casing and is positioned in any blade flow channel of the n + m-th stage stator of the gas compressor; or the position of the n + m stage rotor blade of the compressor in the axial projection range of the casing; wherein n is more than or equal to 1, and m is more than or equal to 1;
all the oscillating jet flow outlets are arranged on the inner wall of the casing, and at least one oscillating jet flow outlet is positioned in any blade flow channel in the nth stage stator of the gas compressor; or the position of the n-th stage rotor blade of the compressor in the axial projection range of the casing.
First preferred mode of the fluidic oscillator flow channel:
the fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel and a second outlet airflow bleed air channel; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the second outlet airflow bleed air channel;
the first outlet airflow bleed air channel is provided with a first feedback outlet; the second outlet airflow bleed air channel is provided with a second feedback outlet; the outlet of the inlet airflow bleed air channel is communicated with a first feedback return port and a second feedback return port;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
Second preferred mode of the fluidic oscillator flow channel:
the fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel and a second outlet airflow bleed air channel; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the second outlet airflow bleed air channel;
the outlet of the inlet airflow bleed air channel is communicated with a first feedback port and a second feedback port; the first feedback port is in communication with the second feedback port through one of the feedback channels.
A third preferred mode of the fluidic oscillator flow channel:
the fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel, a second outlet airflow bleed air channel and a flow chamber; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel, the flow chamber and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel, the flow chamber and the second outlet airflow bleed air channel;
the flow chamber is provided with a first feedback outlet and a second feedback outlet at the position close to the outlet of the flow chamber; the outlet of the inlet airflow bleed air channel is communicated with a first feedback return port and a second feedback return port;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
For the above three preferred fluidic oscillator flow channels:
further, the first oscillating jet flow outlet and the second oscillating jet flow outlet are respectively positioned in any two adjacent blade runners in the nth stage stator of the gas compressor;
or respectively located at the position of any two adjacent rotor blades of the nth stage of the compressor in the axial projection range of the casing.
Further, the first oscillating jet flow outlet is located in any one blade flow channel of the nth stage stator of the compressor, and the second oscillating jet flow outlet is located in the axial projection range of the nth stage rotor of the compressor on the casing.
A fourth preferred mode of the fluidic oscillator flow channel:
the fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, an outlet airflow bleed air channel and a flow chamber; the number of the oscillating jet flow outlets is one;
the oscillating jet flow bleed air inlet is communicated with the oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the flow chamber;
a first feedback port and a second feedback port are arranged at the position close to the inlet of the flow chamber, and a first feedback outlet and a second feedback outlet are arranged at the position close to the outlet of the flow chamber;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
Aiming at the preferable mode of the flow channels of the four fluid oscillators, furthermore, the included angle between the flow direction of the airflow in the flow channels of the fluid oscillators and the flow direction of the main flow in the compressor is b, and b is more than or equal to 0 degree and less than or equal to 180 degrees.
Furthermore, the included angle between the flow channel direction of the oscillating jet flow outlet and the main flow axial direction of the air compressor is a, and a is more than or equal to 0 degree and less than or equal to 180 degrees.
An air compressor comprises any one of the casings.
A method for expanding stability of an air compressor is characterized in that according to the number and distribution conditions of corresponding stators and blades of the air compressor, a corresponding number of flow channels of a fluid oscillator are arranged in a casing to construct any casing;
an air flow enters the compressor and enters a flow channel of the fluid oscillator from an oscillation jet flow bleed air inlet of the casing, which is positioned between the nth + m-stage stator or the nth + m-stage rotor;
after the airflow is subjected to self-circulation oscillation through a flow channel of the fluid oscillator, oscillation jet flow is formed at an oscillation jet flow outlet, so that the flow separation of an angular region of a stator and the flow separation of a suction surface corresponding to the oscillation jet flow outlet are reduced, or the secondary flow of a blade tip gap of a rotor corresponding to the oscillation jet flow outlet is reduced, and the stable working margin of the gas compressor is improved;
meanwhile, the pressure of the oscillation jet flow bleed air inlet is greater than that of an oscillation jet flow outlet between the nth-stage stator or the nth-stage rotor;
when the oscillating jet flow bleed air inlet is positioned between the nth and the mth stages of stators, the flow channel of the fluid oscillator generates a suction effect on the boundary layer at the top end of the nth and the mth stages of stators so as to reduce the flow separation of the nth and the mth stages of stators; generating a stability expansion effect; or
When the oscillating jet flow bleed air inlet is positioned between the n + m-th-stage rotors, the fluid oscillator generates a suction effect on the secondary flow at the top ends of the n + m-th-stage rotors, so that the leakage flow of blade tips of the rotors is reduced; the stability expanding effect is generated.
Compared with the prior art, the present disclosure has at least the following advantages:
according to the number and the distribution condition of corresponding stator and rotor blades of an air compressor, a fluid oscillator flow channel is arranged in a casing, and air flow enters the fluid oscillator flow channel from an oscillation jet flow bleed air inlet between an n + m-stage stator or an n + m-stage rotor of the casing; because the pressure of the oscillating jet flow bleed air inlet is greater than that of the oscillating jet flow outlet positioned between the nth stage stator or the rotor, the airflow forms an oscillating jet flow at the oscillating jet flow outlet positioned between the nth stage stator of the casing after passing through the flow channel of the fluid oscillator under the action of the pressure difference between the rear stage and the front stage of the air compressor, so that the angular region flow separation and the suction surface flow separation of the oscillating jet flow outlet corresponding to the top end of the stator blade grid are reduced; or an oscillating jet is formed at an oscillating jet outlet positioned at the top end of the nth-stage rotor of the casing, and secondary flow of a blade top gap of the oscillating jet outlet corresponding to the top end of the rotor blade is reduced, so that the stable working margin of the gas compressor is improved; because the pressure of the oscillation jet flow bleed air inlet is greater than the pressure of the oscillation jet flow outlet positioned between the nth stator or the nth rotor, when the oscillation jet flow bleed air inlet is positioned between the nth + mth stage stator or the nth rotor, the flow channel of the fluid oscillator generates a suction effect on the boundary layer at the top end of the nth + mth stage stator or the nth rotor and the secondary flow, and the flow separation of the n + mth stage stator or the nth rotor is reduced; the stability expanding effect is generated.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a schematic illustration of a barrel construction of the present disclosure;
FIG. 2 is a schematic view of the structure in the direction A of FIG. 1;
FIG. 3 is a schematic view of a flow passage structure of a fluidic oscillator according to a first embodiment;
FIG. 4 is a schematic cross-sectional view of an oscillating jet outlet;
FIG. 5 is a schematic diagram of a typical velocity response of a single outlet of a pulsed fluidic oscillator at an inlet pressure of 1.0bar gauge and air as the working medium;
FIG. 6 is a schematic diagram of an embodiment of the present invention when the flow direction A1 of the gas flowing through the flow channel of the fluidic oscillator is the same as the flow direction C1 of the main gas flowing through the compressor;
FIG. 7 is a schematic structural view of the second embodiment;
FIG. 8 is a schematic view of a flow channel structure of a fluidic oscillator according to a third embodiment;
FIG. 9 is a schematic view of a flow channel structure of a fluidic oscillator according to a fourth embodiment;
FIG. 10 is a schematic structural view of the fifth embodiment;
FIG. 11 is a schematic structural diagram of the fifth embodiment when the flow direction of the gas in the flow passage of the fluidic oscillator is the same as the main flow direction in the compressor;
FIG. 12 is a schematic view showing the shape of a water flow developing sweep flow at the outlet of a flow channel of a sweep-type fluidic oscillator according to a fifth embodiment;
the flow control device comprises a casing 1, a fluidic oscillator flow channel 2, an oscillating jet bleed air inlet 3, an oscillating jet outlet 4, a first oscillating jet outlet 41, a second oscillating jet outlet 42, a feedback channel 5, a first feedback channel 51, a second feedback channel 52, a first feedback outlet 511, a second feedback outlet 521, a first feedback return port 512, a second feedback return port 522, a first feedback port 53, a second feedback port 54, an inlet airflow bleed air channel 6, a first outlet airflow bleed air channel 71, a second outlet airflow bleed air channel 72, a stator 81, a rotor 82, blades 9 and a flow chamber 91.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Example one
Referring to fig. 1 and 2, a casing 1 based on self-circulation oscillation jet flow is provided, wherein a fluid oscillator flow channel 2 is arranged in the casing 1; in this embodiment, the fluid oscillator channel 2 is a pulsed jet oscillator channel, and is characterized in that: comprises an inlet and two outlets. Under steady-state inlet conditions, i.e. with no change in the inlet flow, the main flow exits alternately at the two outlets, at each outlet, in the direction of the outlet channel, a pulsed jet is formed.
Referring to fig. 1 and 2, a flow channel 2 of a fluidic oscillator according to the present embodiment includes: an oscillating jet bleed air inlet 3, an oscillating jet outlet 4, and two feedback channels 5 for feeding back part of the jet flowing from the oscillating jet bleed air inlet 3 to the oscillating jet outlet 4 to the connection between the oscillating jet bleed air inlet 3 and the oscillating jet outlet 4.
With reference to fig. 2 and 3, the oscillating jet outlet 4 comprises: a first oscillating jet outlet 41 and a second oscillating jet outlet 42; the two feedback channels 5 are a first feedback channel 51 and a second feedback channel 52, respectively.
Referring to fig. 2 and 3, the fluidic oscillator flow channel 2 further includes: an inlet airflow bleed air duct 6, a first outlet airflow bleed air duct 71, a second outlet airflow bleed air duct 72; the oscillating jet flow bleed air inlet 3 is communicated with the first oscillating jet flow outlet 41 sequentially through the inlet airflow bleed air channel 6 and the first outlet airflow bleed air channel 71; the oscillating jet bleed air inlet 3 is communicated with the second oscillating jet outlet 42 sequentially through the inlet airflow bleed air channel 6 and the second outlet airflow bleed air channel 72;
the first outlet airflow bleed air channel 71 is provided with a first feedback outlet 511; the second outlet airflow bleed air channel 72 is provided with a second feedback outlet 521; the outlet of the inlet airflow bleed air channel 6 is communicated with a first feedback return port 512 and a second feedback return port 522; the first feedback outlet 511 is communicated with the first feedback port 512 through the first feedback channel 51; the second feedback outlet 521 communicates with the second feedback port 522 through the second feedback passage 52.
Referring to fig. 1-3, the oscillating jet bleed air inlet 3 is arranged on the inner wall of the casing 1 and is located at a position in any one of the blade runners 81 of the n + m-th stator stage of the compressor or at a position in the axial projection range of the blades 9 of the n + m-th rotor stage 82 of the compressor on the casing, for example, as shown in fig. 2, the oscillating jet bleed air inlet 3 is located at a position at the tip of any one of the blades 9 of the n + m-th stator stage of the compressor or the n + m-th rotor stage 82 of the compressor; the optimal position of the oscillating jet flow bleed air inlet 3 is between 0 and 1.1 times of chord length in the axial direction of the corresponding blade 9 and between 0 and 1.0 times of grid distance in the circumferential direction; in order to satisfy the pressure difference required for forming the oscillating jet, wherein m is more than or equal to 1; n is more than or equal to 1.
The oscillating jet flow outlet 4 is arranged on the inner wall of the casing 1; the first oscillating jet outlet 41 and the second oscillating jet outlet 42 are respectively positioned at the top ends of any two adjacent blades 9 of the nth stage stator 81 or the nth stage rotor 82 of the compressor. The preferred positions of the first oscillating jet flow outlet 41 and the second oscillating jet flow outlet 42 are between 0 and 1.1 times of chord length in the axial direction and between 0 and 1.0 times of grid distance in the circumferential direction of the corresponding blade 9;
referring to fig. 2 and 4, the included angle between the flow direction a1 of the gas flow in the flow channel 2 of the fluidic oscillator and the flow direction C1 of the main flow in the compressor is b, wherein b is greater than or equal to 0 degrees and less than or equal to 180 degrees; the air flow direction a1 in the fluidic oscillator flow channel 2 is the vector direction of the symmetry axis of the oscillating jet outlet 4, which takes the center of the oscillating jet bleed air inlet 3 as the starting point. The included angle between the flow channel direction B1 of the oscillating jet flow outlet 4 and the axial direction of the main flow of the compressor is a, and a is more than or equal to 0 degree and less than or equal to 180 degrees.
Referring to fig. 2, in this embodiment, when m is 2, the oscillating jet bleed air inlet 3 is located at a position on the side of the tip of any one of the blades 9 of the n +2 th stage stator 81 close to the suction surface. After air is introduced into the casing 1 from the position between the (n + 2) -th stage stator 81, the air flow firstly enters the air inlet air flow introducing channel 6 and then enters the fluidic oscillator flow channel 2, and according to the application condition of actual needs, different frequency responses and speed responses along with the change of inlet pressure can be obtained by designing different geometric dimensions, such as the length or the volume of the feedback channel 5 and the ratio of the inlet cross-sectional area to the outlet cross-sectional area.
Referring to fig. 1 to 5, the fluidic oscillator flow channel 2 is capable of generating self-oscillation by means of the coanda principle of a fluid. So that a high-frequency pulse type oscillating jet similar to that shown in fig. 5 is formed at the first oscillating jet outlet 41 and the second oscillating jet outlet 42 located in the vicinity of the suction surface of the adjacent blade 9 of the nth stage stator 81.
The effect of the inlet air stream bleed air channel 6 and the outlet air stream bleed air channel 7 is to increase the flexibility of the position in which the fluidic oscillator flow channel 2 is arranged in the housing 1. As shown in fig. 2, the flow direction a1 of the gas flow in the flow channel 2 of the fluidic oscillator is opposite to the main flow direction C1 of the compressor, and the direction of the oscillating jet outlet 4 needs to be the same as the main flow direction of the compressor, namely: a < 90. Due to the limitation of the thickness of the casing 1, the requirement that the direction of the oscillating jet flow outlet 4 is the same as the main flow direction of the compressor is difficult to meet only through a radial flow channel in the casing 1, in order to get rid of the limitation of the thickness of the casing 1, the direction of the air flow of the oscillating jet flow outlet 4 can be changed from the direction opposite to the main flow direction of the compressor to be vertical to the main flow direction by extending and bending the outlet air flow bleed channel, and then the required direction of the oscillating jet flow outlet 4 is realized through the radial flow channel in the casing 1.
As shown in fig. 6, the airflow direction a1 in the fluidic oscillator channel 2 is the same as the main airflow direction C1 in the compressor, and the oscillating jet bleed air inlet 3 is also located at the upstream position of the oscillating jet outlet 4, so that the high-pressure airflow located downstream of the controlled point is guided to the upstream position of the controlled point by extending and bending the inlet airflow bleed air channel 6, so that the airflow direction in the fluidic oscillator channel 2 is the same as the main airflow direction in the compressor, and the difficulty and flow loss in changing the airflow direction of the oscillating jet outlet 4 to the required jet outlet direction are reduced.
In this embodiment, due to the coanda effect of the fluid oscillator flow passage 2 and the pressure difference between the n + m-th stator 81 or the n + m-th rotor 82 and the n-th stator 81 or the n-th rotor 82, a pulse type oscillating jet similar to that shown in fig. 5 is formed at each outlet, that is, the direction of the velocity is constant, and the absolute value of the velocity oscillates at a certain frequency within a certain range. The pulse oscillation jet flow at the two oscillation jet flow outlets 4 can reduce the flow separation at the top end of the corresponding cascade, namely, reduce the flow separation at the corner area of the stator 81 or reduce the tip leakage flow of the rotor 82, thereby improving the stable working margin of the compressor.
Example two
Referring to fig. 7, the present embodiment is substantially the same as the first embodiment, except that: the first oscillating jet flow outlet 41 and the second oscillating jet flow outlet 42 are respectively located at positions in the flow channel of any two adjacent blades 9 in the nth stage stator 81 of the compressor, or are respectively located at positions in the axial projection range of any two adjacent rotor blades on the casing of the nth stage stator of the compressor. For example, referring to fig. 7, the first oscillating jet outlet 41 is located at the tip of any one of the blades 9 of the stator 81 of the n-th stage of the compressor, and the second oscillating jet outlet 42 is located at the tip of any one of the blades 9 of the rotor 82 of the n-th stage of the compressor.
EXAMPLE III
In this embodiment, the fluidic oscillator channel 2 is a pulsed fluidic oscillator channel, and referring to fig. 8, the difference is that the outlet of the inlet airflow bleed air channel 6 of the fluidic oscillator channel 2 is communicated with a first feedback port 53 and a second feedback port 54; the first feedback port 53 communicates with the second feedback port 54 through one of the feedback passages 5.
Example four
In this embodiment, the fluid oscillator channel 2 is a pulsed fluidic oscillator channel, and the difference with reference to fig. 9 is that:
the fluidic oscillator flow channel 2 further includes: a flow chamber 91;
the oscillating jet flow bleed air inlet 3 is communicated with the first oscillating jet flow outlet 41 sequentially through the inlet airflow bleed air channel 6, the flow chamber 91 and the first outlet airflow bleed air channel 71; the oscillating jet bleed air inlet 3 is communicated with the second oscillating jet outlet 42 sequentially through the inlet airflow bleed air channel 6, the flow chamber 91 and the second outlet airflow bleed air channel 72;
the flow chamber 91 is provided with a first feedback outlet 511 and a second feedback outlet 521 at positions close to the outlets thereof; the outlet of the inlet airflow bleed air channel 6 is communicated with a first feedback return port 512 and a second feedback return port 522;
the two feedback channels 5 are respectively a first feedback channel 51 and a second feedback channel 52, and the first feedback outlet 511 is communicated with the first feedback return port 512 through the first feedback channel 51; the second feedback outlet 521 communicates with the second feedback port 522 through the second feedback passage 52.
EXAMPLE five
Referring to fig. 1, 10 and 11, the present embodiment provides a casing 1 based on self-circulation oscillation jet, wherein a fluidic oscillator channel 2 is disposed in the casing 1; the fluidic oscillator channel 2 is a sweep fluidic oscillator channel 2, and unlike the first embodiment, the number of the oscillation jet outlets 4 of the fluidic oscillator channel 2 is one, and the fluidic oscillator channel 2 further includes a flow chamber 91;
the oscillating jet flow bleed air inlet 3 is communicated with the oscillating jet flow outlet 4 sequentially through the inlet airflow bleed air channel 6 and the flow chamber 91; the fluidic oscillator channel 2 in this embodiment has no outlet airflow bleed air channel;
a first feedback outlet 511 and a second feedback outlet 521 are arranged at the positions close to the inlet of the flow chamber 91 and the outlet of the flow chamber 91;
the two feedback channels 5 are respectively a first feedback channel 51 and a second feedback channel 52, and the first feedback outlet 511 is communicated with the first feedback return port 512 through the first feedback channel 51; the second feedback outlet 521 communicates with the second feedback port 522 through the second feedback passage 52.
Referring to fig. 10 and 11, taking m-2 as an example, the sweep-type fluidic oscillator channel 2 also has an oscillating jet inlet 3, similar to the pulse-type fluidic oscillator channel 2, and the inlet airflow bleed air passage 6 communicates with the oscillating jet bleed air inlet 3 on the suction surface side of any one of the blades 9 of the n +2 stage stator 81. The difference is that the flow channel 2 of the sweep-type fluidic oscillator has only one outlet, and due to the characteristics of the sweep-type oscillating jet, the outlet is the oscillating jet outlet 4 of the flow channel in the casing 1, and an outlet airflow bleed air channel is not arranged in the middle. The oscillating jet outlet 4 is positioned on the suction surface side of the n-th stage stator 81 blade 9 corresponding to the oscillating jet bleed air inlet 3. In order to enable the direction of the outlet jet flow to form a certain angle with the axial direction of the main flow of the compressor, as shown in fig. 4, a is more than or equal to 0 degrees and less than or equal to 180 degrees, and the plane of the expansion section of the outlet of the sweep type fluid oscillator also needs to form a certain angle with the plane of the core part of the oscillator so as to meet the requirement of the angle a.
In the case 1 based on the self-circulation oscillating jet flow of the embodiment, under the action of the pressure difference between the nth + m-stage stator 81 or rotor 82 and the nth-stage stator 81 or rotor 82 and the fluid coanda effect in the flow channel, a sweeping type oscillating jet flow similar to that in fig. 12 is formed at the outlet, that is, the absolute value of the velocity is unchanged, and the direction of the velocity oscillates at a certain frequency within a certain included angle range in a plane from 20 ° to 160 °. The swept-type oscillating jet flow at the outlet can reduce the flow separation at the top end of the corresponding cascade, namely, the flow separation at the corner area of the stator 81 or the leakage flow at the blade tip of the rotor 82, so that the stable working margin of the compressor is improved.
EXAMPLE six
The embodiment provides a compressor, which comprises the casing 1 in any one of the above embodiments. By combining the internal flow channel of the fluidic oscillator with the design of the compressor casing 1, self-circulating oscillating jet flow is formed in the movable blade top area or the static blade angle area of the compressor, and the pressure ratio/efficiency of the compressor and the working margin of the compressor can be improved greatly on the premise of not increasing the complexity of the existing structure.
Meanwhile, the advantages of high active flow control efficiency, high reliability and high safety of passive flow control are combined, and a good effect of active control is obtained in a passive control mode. The method can be applied to an aircraft engine compressor, can obviously improve the working efficiency and the stall margin, simultaneously considers the safety, the reliability and the complexity of a system structure, and has wide prospect in the practical engineering application.
EXAMPLE seven
A method for stabilizing an air compressor is characterized in that a certain number of fluid oscillator runners 2 are arranged in a casing 1 according to the number and distribution conditions of stators 81 and blades 9 of the air compressor, and the casing 1 in any one of the embodiments is constructed;
a gas flow enters the compressor and enters a flow channel 2 of the fluidic oscillator from an oscillating jet bleed air inlet 3 of the casing 1, which is positioned between an n + m-th stage stator 81 or an n + m-th stage rotor 82;
after the airflow is subjected to self-circulation oscillation through the flow channel 2 of the fluid oscillator, oscillation jet flow is formed at the oscillation jet flow outlet 4, and the flow separation of the oscillation jet flow outlet 4 corresponding to the top end of the blade cascade is reduced, so that the stable working margin of the gas compressor is improved;
meanwhile, because the pressure of the oscillating jet flow bleed air inlet 3 is smaller than the pressure of the oscillating jet flow outlet 4 between the nth-stage stator 81 and the nth-stage rotor 82, when the oscillating jet flow bleed air inlet 3 is positioned between the (n + m) -stage stator 81, the fluid oscillator flow channel 2 generates a suction effect on the boundary layer at the top end of the (n + m) -stage stator 81, so that the flow separation of the stator is reduced, and a stability expansion effect is generated; or when the oscillating jet flow bleed air inlet 3 is positioned between the n + m-th stage rotors 82, the fluid oscillator generates suction effect on the boundary layer at the top ends of the n + m-th stage rotors 82, so that the tip leakage flow of the rotors is reduced, and the stability expanding effect is generated.
In practical application, a reasonable number of self-circulation oscillation jet flow channels are arranged according to the number and distribution of the compressor stators 81 and the blades 9. For the pulse oscillation jet, assuming that the n-th stage stationary blade includes 20 blades 9, 10 sets of self-circulation pulse oscillation jet flow channels should be axially symmetrically arranged along the circumferential direction of the casing 1 according to the flow channel structure of fig. 2 and 6; if one outlet is positioned between the stators 81 and the other outlet is positioned between the rotors 82, 20 groups of self-circulation pulse oscillation jet flow channels are axially symmetrically arranged along the circumferential direction of the casing 1; for the swept oscillating jet, 20 sets of self-circulation pulse oscillating jet flow channels are arranged axially symmetrically along the circumferential direction of the casing 1 according to the flow channel structure of fig. 10 and 11.
In the description of the present specification, the terms "first", "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.
Claims (11)
1. A casing based on self-circulation oscillation jet flow is characterized in that a fluid oscillator flow channel is arranged in the casing; the fluidic oscillator flow channel includes: the jet control system comprises an oscillating jet bleed air inlet, at least one oscillating jet outlet and two feedback channels, wherein the two feedback channels are used for feeding back part of jet which flows from the oscillating jet bleed air inlet to the oscillating jet outlet to a connecting part between the oscillating jet bleed air inlet and the oscillating jet outlet;
the oscillating jet flow bleed air inlet is arranged on the inner wall of the casing and is positioned in any blade flow channel of the n + m-th stage stator of the gas compressor; or the position of the n + m stage rotor blade of the compressor in the axial projection range of the casing; wherein n is more than or equal to 1, and m is more than or equal to 1;
all the oscillating jet flow outlets are arranged on the inner wall of the casing, and at least one oscillating jet flow outlet is positioned in any blade flow channel in the nth stage stator of the gas compressor; or the position of the n-th stage rotor blade of the compressor in the axial projection range of the casing.
2. The self-circulating oscillating jet based casing of claim 1, wherein said fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel and a second outlet airflow bleed air channel; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the second outlet airflow bleed air channel;
the first outlet airflow bleed air channel is provided with a first feedback outlet; the second outlet airflow bleed air channel is provided with a second feedback outlet; the outlet of the inlet airflow bleed air channel is communicated with a first feedback return port and a second feedback return port;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
3. The self-circulating oscillating jet based casing of claim 1, wherein said fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel and a second outlet airflow bleed air channel; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the second outlet airflow bleed air channel;
the outlet of the inlet airflow bleed air channel is communicated with a first feedback port and a second feedback port; the first feedback port is in communication with the second feedback port through one of the feedback channels.
4. The self-circulating oscillating jet based casing of claim 1, wherein said fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, a first outlet airflow bleed air channel, a second outlet airflow bleed air channel and a flow chamber; the oscillating jet outlet comprises: a first oscillating jet outlet and a second oscillating jet outlet;
the oscillating jet flow bleed air inlet is communicated with the first oscillating jet flow outlet sequentially through the inlet airflow bleed air channel, the flow chamber and the first outlet airflow bleed air channel; the oscillating jet flow bleed air inlet is communicated with the second oscillating jet flow outlet sequentially through the inlet airflow bleed air channel, the flow chamber and the second outlet airflow bleed air channel;
the flow chamber is provided with a first feedback outlet and a second feedback outlet at the position close to the outlet of the flow chamber; the outlet of the inlet airflow bleed air channel is communicated with a first feedback return port and a second feedback return port;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
5. The self-circulating oscillating jet based casing according to any one of claims 2-4, wherein the first oscillating jet outlet and the second oscillating jet outlet are respectively located at any two adjacent blade runners in the nth stage stator of the compressor;
or respectively located at the position of any two adjacent rotor blades of the nth stage of the compressor in the axial projection range of the casing.
6. The self-circulating oscillating jet based casing according to any one of claims 2-4, wherein the first oscillating jet outlet is located at a position in any one of blade flow passages of the compressor nth stage stator, and the second oscillating jet outlet is located at a position in the axial projection range of the compressor nth stage rotor on the casing.
7. The self-circulating oscillating jet based casing of claim 1, wherein said fluidic oscillator flow channel further comprises: the air conditioner comprises an inlet airflow bleed air channel, an outlet airflow bleed air channel and a flow chamber; the number of the oscillating jet flow outlets is one;
the oscillating jet flow bleed air inlet is communicated with the oscillating jet flow outlet sequentially through the inlet airflow bleed air channel and the flow chamber;
a first feedback port and a second feedback port are arranged at the position close to the inlet of the flow chamber, and a first feedback outlet and a second feedback outlet are arranged at the position close to the outlet of the flow chamber;
the two feedback channels are respectively a first feedback channel and a second feedback channel, and the first feedback outlet is communicated with the first feedback return port through the first feedback channel; the second feedback outlet is communicated with the second feedback return port through the second feedback channel.
8. A self-circulating oscillating jet based casing according to any of claims 1-4 and 7, wherein the flow direction of the gas flow in the flow channel of the fluidic oscillator is at an angle b of 0 ° to 180 ° to the main flow direction of the compressor.
9. The self-circulating oscillating jet based casing according to any one of claims 1-4 and 7, wherein the flow channel direction of the oscillating jet outlet and the main flow axial direction of the compressor form an included angle a, and the included angle a is more than or equal to 0 degrees and less than or equal to 180 degrees.
10. A compressor, characterized by comprising a casing according to any one of claims 1 to 9.
11. A method for stabilizing an air compressor, characterized in that a casing according to any one of claims 1-9 is constructed by arranging a corresponding number of channels of a fluidic oscillator in the casing according to the number and distribution of stators and blades of the air compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010699826.7A CN111810454A (en) | 2020-07-17 | 2020-07-17 | Casing, compressor and stability expanding method based on self-circulation oscillation jet flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010699826.7A CN111810454A (en) | 2020-07-17 | 2020-07-17 | Casing, compressor and stability expanding method based on self-circulation oscillation jet flow |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111810454A true CN111810454A (en) | 2020-10-23 |
Family
ID=72866218
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010699826.7A Pending CN111810454A (en) | 2020-07-17 | 2020-07-17 | Casing, compressor and stability expanding method based on self-circulation oscillation jet flow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111810454A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112685966A (en) * | 2020-12-22 | 2021-04-20 | 中国船舶重工集团公司第七0三研究所 | Design method of self-circulation type treatment casing of gas compressor of ship gas turbine |
| CN113236372A (en) * | 2021-06-07 | 2021-08-10 | 南京航空航天大学 | Gas turbine guide vane blade with jet oscillator and working method |
| CN113280366A (en) * | 2021-05-13 | 2021-08-20 | 中国航空发动机研究院 | Afterburner structure based on self-excitation sweep oscillation fuel nozzle |
| CN113279978A (en) * | 2021-03-23 | 2021-08-20 | 厦门大学 | Gas compressor and method for weakening sound excitation of rotor blade of gas compressor |
| CN113404747A (en) * | 2021-06-29 | 2021-09-17 | 上海交通大学 | Outlet same-phase control and frequency decoupling oscillator |
| CN114370337A (en) * | 2022-01-14 | 2022-04-19 | 中国航空发动机研究院 | Jet oscillator |
| CN114857044A (en) * | 2022-05-13 | 2022-08-05 | 清华大学 | Full-air-floatation supported multistage counter-rotating axial flow compressor |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040081552A1 (en) * | 2002-07-20 | 2004-04-29 | Volker Guemmer | Fluid flow machine with integrated fluid circulation system |
| US20060104805A1 (en) * | 2004-06-24 | 2006-05-18 | Volker Gummer | Turbomachine with means for the creation of a peripheral jet on the stator |
| US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
| CN103314220A (en) * | 2010-10-11 | 2013-09-18 | 空中客车运作有限责任公司 | Fluid actuator for influencing the flow along a flow surface, as well as blow-out device and flow body comprising a like fluid actuator |
| CN103732854A (en) * | 2011-11-11 | 2014-04-16 | 哈里伯顿能源服务公司 | Autonomous fluid control assembly having a movable, density-driven diverter for directing fluid flow in a fluid control system |
| CN103967812A (en) * | 2014-04-29 | 2014-08-06 | 西北工业大学 | Reverse-flow type counter-rotating adsorption gas compressor |
| CN104675755A (en) * | 2015-01-14 | 2015-06-03 | 西北工业大学 | Circumferential staggered self-circulating casing treating method for axial-flow compressor |
| CN105927560A (en) * | 2016-06-28 | 2016-09-07 | 中国科学院工程热物理研究所 | Gas compressor with stability enhancing and effect improving device |
| CN107202036A (en) * | 2017-07-24 | 2017-09-26 | 北京航空航天大学 | It is a kind of at the same improve stator corner region flow self-loopa processor box |
| CN107743422A (en) * | 2015-06-08 | 2018-02-27 | 流体动力有限公司 | Fluidic oscillator |
| CN110145497A (en) * | 2019-05-09 | 2019-08-20 | 西北工业大学 | A self-circulating casing processing and stabilizing device for compressors moving axially forward |
| CN110449309A (en) * | 2019-08-16 | 2019-11-15 | 中国航空发动机研究院 | A kind of fluidic oscillator array and its frequency synchronization method |
| CN110963021A (en) * | 2018-09-28 | 2020-04-07 | 空中客车运作有限责任公司 | Flow conductor for an aircraft |
-
2020
- 2020-07-17 CN CN202010699826.7A patent/CN111810454A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040081552A1 (en) * | 2002-07-20 | 2004-04-29 | Volker Guemmer | Fluid flow machine with integrated fluid circulation system |
| US20060104805A1 (en) * | 2004-06-24 | 2006-05-18 | Volker Gummer | Turbomachine with means for the creation of a peripheral jet on the stator |
| US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
| CN103314220A (en) * | 2010-10-11 | 2013-09-18 | 空中客车运作有限责任公司 | Fluid actuator for influencing the flow along a flow surface, as well as blow-out device and flow body comprising a like fluid actuator |
| CN103732854A (en) * | 2011-11-11 | 2014-04-16 | 哈里伯顿能源服务公司 | Autonomous fluid control assembly having a movable, density-driven diverter for directing fluid flow in a fluid control system |
| CN103967812A (en) * | 2014-04-29 | 2014-08-06 | 西北工业大学 | Reverse-flow type counter-rotating adsorption gas compressor |
| CN104675755A (en) * | 2015-01-14 | 2015-06-03 | 西北工业大学 | Circumferential staggered self-circulating casing treating method for axial-flow compressor |
| CN107743422A (en) * | 2015-06-08 | 2018-02-27 | 流体动力有限公司 | Fluidic oscillator |
| CN105927560A (en) * | 2016-06-28 | 2016-09-07 | 中国科学院工程热物理研究所 | Gas compressor with stability enhancing and effect improving device |
| CN107202036A (en) * | 2017-07-24 | 2017-09-26 | 北京航空航天大学 | It is a kind of at the same improve stator corner region flow self-loopa processor box |
| CN110963021A (en) * | 2018-09-28 | 2020-04-07 | 空中客车运作有限责任公司 | Flow conductor for an aircraft |
| CN110145497A (en) * | 2019-05-09 | 2019-08-20 | 西北工业大学 | A self-circulating casing processing and stabilizing device for compressors moving axially forward |
| CN110449309A (en) * | 2019-08-16 | 2019-11-15 | 中国航空发动机研究院 | A kind of fluidic oscillator array and its frequency synchronization method |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112685966A (en) * | 2020-12-22 | 2021-04-20 | 中国船舶重工集团公司第七0三研究所 | Design method of self-circulation type treatment casing of gas compressor of ship gas turbine |
| CN113279978A (en) * | 2021-03-23 | 2021-08-20 | 厦门大学 | Gas compressor and method for weakening sound excitation of rotor blade of gas compressor |
| CN113279978B (en) * | 2021-03-23 | 2024-01-26 | 厦门大学 | Compressor and method for weakening acoustic excitation of compressor rotor blade |
| US11913409B2 (en) | 2021-05-13 | 2024-02-27 | Aero Engine Academy Of China | Afterburner structure with self-excited sweeping oscillating fuel injection nozzles |
| CN113280366A (en) * | 2021-05-13 | 2021-08-20 | 中国航空发动机研究院 | Afterburner structure based on self-excitation sweep oscillation fuel nozzle |
| CN113280366B (en) * | 2021-05-13 | 2022-09-27 | 中国航空发动机研究院 | Afterburner structure based on self-excitation sweep oscillation fuel nozzle |
| CN113236372B (en) * | 2021-06-07 | 2022-06-10 | 南京航空航天大学 | Gas turbine guide vane blade with jet oscillator and working method |
| CN113236372A (en) * | 2021-06-07 | 2021-08-10 | 南京航空航天大学 | Gas turbine guide vane blade with jet oscillator and working method |
| CN113404747A (en) * | 2021-06-29 | 2021-09-17 | 上海交通大学 | Outlet same-phase control and frequency decoupling oscillator |
| CN114370337A (en) * | 2022-01-14 | 2022-04-19 | 中国航空发动机研究院 | Jet oscillator |
| CN114370337B (en) * | 2022-01-14 | 2023-05-23 | 中国航空发动机研究院 | Jet oscillator |
| CN114857044A (en) * | 2022-05-13 | 2022-08-05 | 清华大学 | Full-air-floatation supported multistage counter-rotating axial flow compressor |
| CN114857044B (en) * | 2022-05-13 | 2023-09-12 | 清华大学 | A multi-stage counter-rotating axial flow compressor with full air flotation support |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111810454A (en) | Casing, compressor and stability expanding method based on self-circulation oscillation jet flow | |
| CN111810295B (en) | Flow separation active control structure, method and application | |
| US2763426A (en) | Means for varying the quantity characteristics of supersonic compressors | |
| RU2379525C2 (en) | Pipe assembly for gas turbine engine, bypass pipe and gas turbine engine | |
| CN110449309B (en) | Fluid oscillator array and frequency synchronization method thereof | |
| EP2090769A1 (en) | Apparatus, method and system for gas turbine engine noise reduction | |
| US5904470A (en) | Counter-rotating compressors with control of boundary layers by fluid removal | |
| JP2008255987A (en) | Mixer for cooling and sealing air system for turbo machine | |
| US11970979B2 (en) | Turbine engine with shockwave attenuation | |
| CN110775283B (en) | Blade assembly for distribution of stratified fluids in an aircraft | |
| US4029430A (en) | Short subsonic diffuser for large pressure ratios | |
| JP2002129903A (en) | Structure of cooling gas turbine blade | |
| CN102094850A (en) | Design method of circumferential discontinuously distributed entraining grooves of engine air system | |
| US10590778B2 (en) | Engine component with non-uniform chevron pins | |
| JP3714784B2 (en) | Cooling flow control for high temperature combustion chambers. | |
| US3357191A (en) | Propulsion means | |
| CN113074047A (en) | S-shaped air inlet channel rotational flow distortion flow control device based on fluid oscillator | |
| Fan et al. | Numerical investigation of the aerodynamic performance and loss mechanism in a low bypass ratio variable cycle engine fan | |
| Iancu et al. | Feasibility study of integrating four-port wave rotors into ultra-micro gas turbines (UmGT) | |
| CN115289499B (en) | Hollow support plate of gas inlet of combustion chamber of gas turbine | |
| EP2306029A1 (en) | Compressor and method for controlling the fluid flow in a compressor | |
| CN114321014B (en) | Local self-circulation flow control structure of radial diffuser of centrifugal compressor | |
| CN109083687B (en) | Method of minimizing cross flow across cooling holes and component for turbine engine | |
| Boehle et al. | Compressible flow in inlet guide vanes with mechanical flaps | |
| CN111691929A (en) | Turbine blade top active flow control method based on sweep frequency type ejector |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |