CN114858426B - A test device for a gas turbine combustion chamber nozzle - Google Patents
A test device for a gas turbine combustion chamber nozzleInfo
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- CN114858426B CN114858426B CN202210293745.6A CN202210293745A CN114858426B CN 114858426 B CN114858426 B CN 114858426B CN 202210293745 A CN202210293745 A CN 202210293745A CN 114858426 B CN114858426 B CN 114858426B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
本发明公开了一种用于燃气轮机燃烧室喷嘴测试装置，所述一种用于燃气轮机燃烧室喷嘴测试装置包括逆向整流部分和均流板。所述逆向整流部分包括喷嘴安装部以及依次连通的第一腔室、过渡腔室和第二腔室，所述第一腔室设在所述过渡腔室的上游，所述第二腔室设在所述过渡腔室的下游，所述第一腔室与助燃气体的气源连通，所述均流板设在所述过渡腔室的出口处和/或所述第二腔室的进口处，所述均流板上具有多个供助燃气体流过的通气孔。本发明实施例的一种用于燃气轮机燃烧室喷嘴测试装置具有可靠性高等优点。
The present invention discloses a device for testing a nozzle in a gas turbine combustion chamber, the device comprising a reverse rectifying portion and a flow equalizing plate. The reverse rectifying portion comprises a nozzle mounting portion and a first chamber, a transition chamber, and a second chamber that are sequentially connected, the first chamber being located upstream of the transition chamber, the second chamber being located downstream of the transition chamber, the first chamber being connected to a source of combustion-supporting gas, the flow equalizing plate being located at the outlet of the transition chamber and/or at the inlet of the second chamber, and the flow equalizing plate having a plurality of vents for the combustion-supporting gas to flow through. The device for testing a nozzle in a gas turbine combustion chamber according to an embodiment of the present invention has advantages such as high reliability.
Description
Technical Field
The invention relates to the technical field of combustion of gas turbines, in particular to a nozzle testing device for a combustion chamber of a gas turbine.
Background
The technical development of gas turbine combustors has been kept away from combustor testing, where nozzle performance testing is the most basic means of verifying the feasibility of combustion system design, and uniformity of air flow at the nozzle inlet is an important requirement for nozzle testing. In the related art, the uniformity of air flow at the nozzle opening is low, and the problems of low reliability of test data of the nozzle of the combustion chamber and the like exist.
Disclosure of Invention
The present invention has been made based on the findings and knowledge of the inventors regarding the following facts and problems:
The gas turbine is a rotary internal combustion engine and mainly comprises a gas compressor, a combustion chamber and a turbine. Air reversely flows backwards through the exhaust cavity of the air compressor to enter the annular pipe-shaped combustion chamber, then enters the premixing cavity of the fuel nozzle, and after being mixed with the injected fuel and air, enters the flame tube of the combustion chamber to be combusted, and high-temperature fuel gas is discharged through the transition section.
The development of gas turbine combustors involves both microscopic-scale chemical kinetics and macroscopic turbulent flow, with strong nonlinear coupling of the two. At present, the existing combustion theory and method are difficult to accurately and quantitatively analyze the working characteristics of the combustion chamber including ignition characteristics, stability boundaries, combustion efficiency, structural integrity and the like under real environment conditions, so that a comprehensive optimal design result with low NOx emission, low combustion pulsation, wide working boundaries and long service life is required to be achieved, multiple rounds of design optimization iteration are required, a design scheme is verified and confirmed through numerical simulation, test and other means, the test is a final standard for checking the correctness of the design, and a single-nozzle test study is used for grasping nozzle design criteria and test verification technology to complete the primary design, optimization and perfection of the nozzle design scheme of the combustion chamber.
The test device for developing the nozzle needs to simulate the hydrodynamic process of the nozzle inlet in the real environment to form a required airflow structure. Currently, in the related art, the uniformity of the air flow at the inlet of the nozzle is low, the environment of the inlet of the nozzle is different, and the mixing and distribution of the oil gas of the nozzle are greatly different from those in a real combustion chamber.
The present invention aims to solve at least one of the technical problems in the related art to some extent. To this end, embodiments of the present invention provide a nozzle testing apparatus for a gas turbine combustor. To improve the reliability of the combustor nozzle test data.
The invention discloses a nozzle testing device for a combustion chamber of a gas turbine, which comprises a reverse rectifying part and a flow equalizing plate. The reverse rectifying part comprises a nozzle mounting part and a first chamber, a transition chamber and a second chamber which are sequentially communicated, wherein the nozzle mounting part is used for mounting a nozzle through which fuel flows, the first chamber is arranged at the upstream of the transition chamber, the second chamber is arranged at the downstream of the transition chamber, the first chamber is communicated with a gas source of combustion-supporting gas, the flow direction of the combustion-supporting gas in the first chamber is intersected with the flow direction of the combustion-supporting gas in the second chamber, the flow direction of the combustion-supporting gas in the transition chamber is intersected with the flow direction of the combustion-supporting gas in the first chamber, and the flow direction of the combustion-supporting gas in the transition chamber is opposite to or intersected with the flow direction of the combustion-supporting gas in the second chamber. The flow equalizing plate is arranged at the outlet of the transition chamber and/or the inlet of the second chamber, and a plurality of vent holes for combustion-supporting gas to flow through are formed in the flow equalizing plate.
In some embodiments, the flow equalizing plates are provided in plurality, at least one of the flow equalizing plates is provided at the outlet of the transition chamber, and at least one of the flow equalizing plates is provided at the inlet of the second chamber.
In some embodiments, the direction of extension of the transition chamber is perpendicular to the direction of extension of the first chamber such that the flow direction of the combustion gas in the first chamber is perpendicular to the flow direction of the combustion gas in the transition chamber, and the direction of extension of the transition chamber is parallel to the direction of extension of the second chamber such that the flow direction of the combustion gas in the second chamber is opposite to the flow direction of the combustion gas in the transition chamber.
In some embodiments, the flow equalization plates disposed at the outlet of the transition chamber are perpendicular to the flow equalization plates disposed at the inlet of the first chamber.
In some embodiments, the flow equalizing plate provided at the outlet of the transition chamber is parallel to the extension direction of the transition chamber, and the flow equalizing plate provided at the inlet of the second chamber is perpendicular to the extension direction of the second chamber.
In some embodiments, the transition chamber and the second chamber are both annular chambers, and the flow equalization plate is an annular flow equalization plate.
In some embodiments, the flow equalizing plate is provided with a plurality of vent hole groups, each vent hole group comprises a plurality of vent holes, and a plurality of vent hole groups are uniformly distributed along the radial direction of the flow equalizing plate at intervals.
In some embodiments, a plurality of the vent holes in the same vent hole group are uniformly distributed along the circumferential direction of the flow equalizing plate at intervals.
In some embodiments, the sum of the flow areas of a plurality of said vents in any one of said vent groups is equal to the sum of the flow areas of a plurality of said vents in any other of said vent groups.
In some embodiments, the reverse rectifying portion further includes a first cylinder, a second cylinder, an annular first sealing plate, and an annular second sealing plate, the first cylinder being sleeved outside the second cylinder, the first cylinder and the second cylinder being disposed at intervals in an inner-outer direction, the first cylinder having a first port and a second port opposite in an extending direction thereof, the second cylinder having a third port and a fourth port opposite in an extending direction thereof, the fourth port being located between the first port and the second port in the extending direction of the first cylinder, and the first port being located between the third port and the fourth port in the extending direction of the first cylinder.
The first shrouding with the second shrouding is followed the extending direction interval of first barrel sets up, the outer end of first shrouding with first barrel links to each other, the inner of first shrouding with the second barrel links to each other, the second shrouding with the second barrel is followed the extending direction interval of first barrel sets up, the outer end of second shrouding with first barrel links to each other, the inner of second shrouding extends to the inside of second barrel, so that first barrel the second barrel the first shrouding with define between the second shrouding the transition cavity.
The first cylinder is provided with an opening communicated with the first cavity, the opening forms an inlet of the transition cavity, an outlet of the transition cavity is defined between the second cylinder and the second sealing plate, and the second cavity is located in the second cylinder.
In some embodiments, the reverse rectifying portion further includes a third cylinder, the second cylinder is sleeved outside the third cylinder, the third cylinder and the second cylinder are disposed at intervals in an inner-outer direction, the third cylinder has a fifth port and a sixth port opposite to each other in an extending direction of the first cylinder, the fifth port is located between the third port and the fourth port in the extending direction of the first cylinder, the fifth port is disposed closer to the third port than the sixth port in the extending direction of the first cylinder, an inner end of the second sealing plate is connected to the third cylinder, and the second chamber is defined among the second cylinder, the second sealing plate and the third cylinder.
In some embodiments, the reverse rectifying portion further comprises a third chamber disposed downstream of the second chamber, the flow direction of the combustion gas in the third chamber being opposite to the flow direction of the combustion gas in the second chamber.
In some embodiments, the reverse rectifying portion further comprises a third annular sealing plate sealed at the third port, the third sealing plate having an inner bore through which at least a portion of the nozzle passes such that the third barrel and the nozzle define the third chamber.
In some embodiments, a combustion gas conduit is also included, the combustion gas conduit being disposed upstream of the transition chamber, at least a portion of the combustion gas conduit defining the first chamber.
In some embodiments, the combustion-supporting gas line is provided in plural, and the plural combustion-supporting gas lines are arranged at intervals along the circumferential direction of the nozzle mounting portion.
Drawings
FIG. 1 is a front view of a nozzle testing apparatus for a combustion chamber of a gas turbine in accordance with an embodiment of the present invention.
FIG. 2 is a right side view of a nozzle testing apparatus for a gas turbine combustor in accordance with an embodiment of the present invention.
FIG. 3 is a schematic view of a first flow straightener for a gas turbine combustor nozzle test apparatus in accordance with an embodiment of the present invention.
FIG. 4 is a schematic illustration of a second flow straightener for a gas turbine combustor nozzle test arrangement in accordance with an embodiment of the present invention.
Reference numerals:
a nozzle test apparatus 100 for a gas turbine combustor;
A reverse rectifying portion 1, a nozzle mounting portion 101, a first chamber 102, a transition chamber 103, a second chamber 104, a third chamber 105, a fourth chamber 106, a fifth chamber 107;
a nozzle 2;
The flow equalizing plate 3, the first flow equalizing plate 301, the first vent 3011, the second flow equalizing plate 302 and the second vent 3021;
A first cylinder 4, a first port 401, a second port 402;
a second cylinder 5, a third port 501, a fourth port 502;
a third cylinder 6, a fifth port 601, a sixth port 602;
A first closing plate 7;
a second closing plate 8;
A third closure plate 9;
the combustion-supporting gas pipeline 10, a first pipe section 1001, a second pipe section 1002 and a third pipe section 1003;
an intake portion 11;
combustion section 12, small diameter section 1201, large diameter section 1202.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
The technical scheme of the present application will be described in detail with reference to the accompanying drawings.
As shown in fig. 1 to 4, a nozzle testing apparatus 100 for a combustion chamber of a gas turbine according to an embodiment of the present invention includes a reverse rectifying portion 1 and a flow equalizing plate 3.
The reverse rectifying portion 1 includes a nozzle mount 101, a first chamber 102, a transition chamber 103, and a second chamber 104 that are sequentially communicated. The nozzle mounting portion 101 is used for mounting the nozzle 2 through which the fuel flows, the first chamber 102 is provided upstream of the transition chamber 103, the second chamber 104 is provided downstream of the transition chamber 103, and the first chamber 102 is in communication with a source of combustion-supporting gas. The flow direction of the combustion-supporting gas in the first chamber 102 is intersected with the flow direction of the combustion-supporting gas in the second chamber 104, the flow direction of the combustion-supporting gas in the transition chamber 103 is intersected with the flow direction of the combustion-supporting gas in the first chamber 102, and the flow direction of the combustion-supporting gas in the transition chamber 103 is opposite to or intersected with the flow direction of the combustion-supporting gas in the second chamber 104.
The flow equalizing plate 3 is arranged at the outlet of the transition chamber 103 and/or at the inlet of the second chamber 104, and a plurality of vent holes for the combustion-supporting gas to flow through are arranged on the flow equalizing plate 3.
The flow equalizing plate 3 is arranged at the outlet of the transition chamber 103 and/or at the inlet of the second chamber 104, which means that the flow equalizing plate 3 is arranged only at the outlet of the transition chamber 103, or the flow equalizing plate is arranged only at the inlet of the second chamber 104, or the flow equalizing plate 3 is arranged at both the outlet of the transition chamber 103 and the inlet of the second chamber 104. By means of the flow equalization plates 3 arranged at the outlet of the transition chamber 103 and/or at the inlet of the second chamber 104, a better homogeneity of the combustion gas at the outlet of the second chamber 104 can be achieved.
When the nozzle 2 performance is detected by using the nozzle testing device 100 for the combustion chamber of the gas turbine, the nozzle 2 to be detected is installed on the nozzle installation part 101. Fuel enters the nozzle through the inlet of the nozzle 2. The combustion gas enters the first chamber 102 through the inlet of the first chamber 102, after which the combustion gas enters the transition chamber 103 and the second chamber 104 in sequence. When the combustion-supporting gas flowing out of the outlet of the second chamber 104 is mixed with the fuel sprayed out of the outlet of the nozzle 2, the uniformity of mixing the combustion-supporting gas and the fuel can be improved due to the better uniformity of the combustion-supporting gas at the outlet of the second chamber 104, so that the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine provided by the embodiment of the invention is improved.
Therefore, the device 100 for testing the nozzle of the combustion chamber of the gas turbine has the advantages of high reliability and the like.
Alternatively, the combustion-supporting gas may be compressed air or compressed oxygen, etc.
In some embodiments, the transition chamber 103 and the second chamber 104 are both annular chambers, and the flow equalization plate 3 is an annular flow equalization plate.
By arranging the transition chamber 103 and the second chamber 104 as annular chambers, when the combustion-supporting gas enters the transition chamber 103 from the first chamber 102, the combustion-supporting gas enters the second chamber 104 through the annular flow equalizing plate after annular diffusion, and the combustion-supporting gas entering the second chamber 104 is annular diffused again, so that the flow uniformity of the combustion-supporting gas is improved, the uniformity of mixing the combustion-supporting gas and fuel is improved, and the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine is improved.
In some embodiments, the flow equalization plates 3 are provided in plurality, at least one flow equalization plate 3 is provided at the outlet of the transition chamber 103, and at least one flow equalization plate 3 is provided at the inlet of the second chamber 104.
For example, as shown in fig. 1, two flow equalizing plates 3 are provided, and the two flow equalizing plates 3 are a first flow equalizing plate 301 and a second flow equalizing plate 302, respectively. The first flow equalization plate 301 is disposed at the outlet of the transition chamber 103 and the second flow equalization plate 302 is disposed at the inlet of the second chamber 104. The combustion-supporting gas in the transition chamber 103 flows out of the transition chamber 103 through the first flow equalizing plate 301, so that the flow uniformity of the combustion-supporting gas is improved, and the combustion-supporting gas flowing out of the transition chamber 103 flows into the second chamber 104 through the second flow equalizing plate 302, so that the flow uniformity of the combustion-supporting gas is improved again.
Therefore, the multistage flow equalization plate 3 is arranged to equalize the combustion-supporting gas entering the second chamber 104, so that the flow uniformity of the combustion-supporting gas is further improved, and the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine is further improved.
In some embodiments, the extension direction of the transition chamber 103 is perpendicular to the extension direction of the first chamber 102, such that the flow direction of the combustion-supporting gas in the first chamber 102 is perpendicular to the flow direction of the combustion-supporting gas in the transition chamber 103. The extension direction of the transition chamber 103 is parallel to the extension direction of the second chamber 104, so that the flow direction of the combustion gas in the second chamber 104 is opposite to the flow direction of the combustion gas in the transition chamber 103.
In order to make the solution of the present application easier to understand, the solution of the present application will be further described by taking the case that the extension direction of the transition chamber 103 coincides with the left-right direction and the inside-outside direction, which are directions adjacent to the center line of the first chamber 102 on a plane perpendicular to the center line of the first chamber 102 and which are directions away from the center line of the first chamber 102 on a plane perpendicular to the center line of the first chamber 102, as shown in fig. 1 and 3, as an example.
For example, as shown in fig. 1, the combustion-supporting gas flows into the first chamber 102 from the outside to the inside, the combustion-supporting gas flowing out of the outlet of the first chamber 102 flows into the transition chamber 103 from the left to the right and flows out of the outlet of the transition chamber 103 through the first flow equalizing plate 301, and then the combustion-supporting gas flows into the second chamber 104 from the right to the left through the second flow equalizing plate 302.
Thus, by arranging the flow direction of the combustion-supporting gas in the second chamber 104 opposite to the flow direction of the combustion-supporting gas in the transition chamber 103, the flow uniformity of the combustion-supporting gas is advantageously increased, so that the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine according to the embodiment of the invention is further improved.
Alternatively, the flow equalization plates 3 provided at the outlet of the transition chamber 103 are perpendicular to the flow equalization plates 3 provided at the inlet of the first chamber 102.
For example, the first flow equalization plate 301 is perpendicular to the second flow equalization plate 302.
By vertically arranging the first flow equalizing plate 301 and the second flow equalizing plate 302, the flow uniformity of the combustion-supporting gas is further improved.
In some embodiments, the flow equalization plates 3 provided at the outlet of the transition chamber 103 are parallel to the extension direction of the transition chamber 103, and the flow equalization plates 3 provided at the inlet of the second chamber 104 are perpendicular to the extension direction of the first chamber 102.
For example, as shown in fig. 1,3 and 4, the first flow equalizing plate 301 is an annular flow equalizing plate extending along a left-right direction, in other words, the first flow equalizing plate 301 is a flow equalizing cylinder, an axial direction of the first flow equalizing plate 301 is parallel to the left-right direction, a cylinder wall of the first flow equalizing plate 301 is provided with a plurality of first vent holes 3011, and the first vent holes 3011 extend along an inner-outer direction. The second flow equalizing plate 302 is an annular flow equalizing plate extending along the inner and outer directions, and the second flow equalizing plate 302 has a plurality of second ventilation holes 3021, and the second ventilation holes 3021 extend along the left and right directions.
When the combustion-supporting gas in the annular transition chamber 103 flows out through the first flow equalizing plate 301, the flow uniformity of the combustion-supporting gas in the inner and outer directions is increased by utilizing the first flow equalizing plate 301, and when the combustion-supporting gas flowing out of the transition chamber 103 enters the annular second chamber 104 through the second flow equalizing plate 302, the flow uniformity of the combustion-supporting gas in the left and right directions is increased by utilizing the second flow equalizing plate 302.
Thus, the reliability of a nozzle test apparatus 100 for a gas turbine combustor according to an embodiment of the present invention is further increased by increasing the flow uniformity of combustion gas in the inward-outward direction and the left-right direction.
Alternatively, as shown in fig. 3, the first ventilation holes 3011 of the first flow equalization plate 301 are provided with a plurality of groups, each group of first ventilation holes 3011 includes a plurality of first ventilation holes 3011, the plurality of first ventilation holes 3011 of the same group are uniformly spaced along the circumferential direction of the first flow equalization plate 301, and the plurality of groups of first ventilation holes 3011 are uniformly spaced along the left-right direction.
Alternatively, as shown in fig. 2 and fig. 4, the second ventilation holes 3021 of the second flow equalizing plate 302 are provided with multiple groups, each group of second ventilation holes 3021 includes multiple second ventilation holes 3021, the multiple second ventilation holes 3021 of the same group are uniformly spaced along the circumference of the second flow equalizing plate 302, and the multiple groups of second ventilation holes 3021 are uniformly spaced along the inner and outer directions.
Alternatively, the flow area sum of the plurality of second ventilation holes 3021 in any one group is equal to the flow area sum of the plurality of second ventilation holes 3021 in any other group.
In some embodiments, the reverse rectifying portion 1 further comprises a first cylinder 4, a second cylinder 5, an annular first sealing plate 7, and an annular second sealing plate 8. The first cylinder 4 is sleeved outside the second cylinder 5, and the first cylinder 4 and the second cylinder 5 are arranged at intervals in the inner-outer direction, wherein inward refers to the direction that a plane perpendicular to the axis of the first cylinder 4 is adjacent to the axis of the first cylinder 4, and outward refers to the direction that a plane perpendicular to the axis of the first cylinder 4 is far away from the axis of the first cylinder 4. The first cylinder 4 has a first port 401 and a second port 402 opposite in the extending direction thereof. The second cylinder 5 has a third port 501 and a fourth port 502 opposite in the direction of extension thereof, the fourth port 502 being located between the first port 401 and the second port 402 in the direction of extension of the first cylinder 4, the first port 401 being located between the third port 501 and the fourth port 502 in the direction of extension of the first cylinder 4.
The first shrouding 7 and the second shrouding 8 set up along the extending direction interval of first barrel 4, and the outer end of first shrouding 7 links to each other with first barrel 4, and the inner of first shrouding 7 links to each other with second barrel 5. The second sealing plate 8 and the second cylinder 5 are arranged at intervals along the extending direction of the first cylinder 4, the outer end of the second sealing plate 8 is connected with the first cylinder 4, and the inner end of the second sealing plate 8 extends to the inside of the second cylinder 5 so as to define a transition chamber 103 between the first cylinder 4, the second cylinder 5, the first sealing plate 7 and the second sealing plate 8.
Wherein the first cylinder 4 has an opening communicating with the first chamber 102, the opening forming an inlet for the transition chamber 103, an outlet for the transition chamber 103 being defined between the second cylinder 5 and the second closure plate 8, and the second chamber 104 being located within the second cylinder 5.
For example, as shown in fig. 1, the first port 401 is located at the left end of the second port 402, and the third port 501 is located at the left end of the fourth port 502. The first sealing plate 7 and the second sealing plate 8 are arranged at intervals along the left-right direction, the first sealing plate 7 seals the first port 401, the second sealing plate 8 seals the second port 402 and the fourth port 502, and therefore the transition chamber 103 is defined by the inner peripheral surface of the first cylinder 4, the outer peripheral surface of the second cylinder 5, the right end surface of the first sealing plate 7 and the left end surface of the second sealing plate 8.
Therefore, the first cylinder 4, the second cylinder 5, the first sealing plate 7 and the second sealing plate 8 are arranged, the transition chamber 103 is arranged to be an annular space, and the flow uniformity of combustion-supporting gas is improved, so that the gas turbine combustor nozzle testing device 100 is simple in structure.
Alternatively, the opening on the first cylinder 4 is spaced apart from the first flow equalizing plate 301 in the left-right direction.
For example, as shown in fig. 1, the opening on the first cylinder 4 is located at the left side of the first flow equalizing plate 301, so as to avoid that the combustion-supporting gas of the first chamber 102 directly impacts the first air holes 3011 on the first flow equalizing plate 301, and affects the flow equalizing effect of the first flow equalizing plate 301.
In some embodiments, the reverse rectifying portion 1 further comprises a third cylinder 6. The second cylinder 5 is sleeved outside the third cylinder 6, the third cylinder 6 and the second cylinder 5 are arranged at intervals in the inner and outer directions, the third cylinder 6 is provided with a fifth port 601 and a sixth port 602 which are opposite in the extending direction of the first cylinder 4, the fifth port 601 is positioned between the third port 501 and the fourth port 502 in the extending direction of the first cylinder 4, the fifth port 601 is arranged closer to the third port 501 than the sixth port 602 in the extending direction of the first cylinder 4, the inner end of the second sealing plate 8 is connected with the third cylinder 6, and a second chamber 104 is defined among the second cylinder 5, the second sealing plate 8 and the third cylinder 6.
For example, as shown in fig. 1, the fifth port 601 and the sixth port 602 are arranged at intervals in the left-right direction, and the fifth port 601 is located on the left side of the sixth port 602. The third port 501 and the fifth port 601 are disposed at intervals in the left-right direction, and the third port 501 is located on the left side of the fifth port 601. The second chamber 104 is defined between the inner peripheral surface of the second cylinder 5, the outer peripheral surface of the third cylinder 6, and the left end surface of the second sealing plate 8.
Thus, by providing the third cylinder 6 and disposing the second chamber 104 as an annular space, the combustion-supporting gas flow uniformity is improved, and the combustion-supporting gas nozzle testing device 100 for a gas turbine in the embodiment of the invention has a simple structure.
Alternatively, each of the first cylinder 4, the second cylinder 5, and the third cylinder 6 is coaxially disposed.
In some embodiments, the reverse rectifying portion 1 further comprises a third chamber 105, the third chamber 105 being arranged downstream of the second chamber 104, the flow direction of the combustion gas in the third chamber 105 being opposite to the flow direction of the combustion gas in the second chamber 104.
For example, as shown in fig. 1, the combustion-supporting gas passes through the chamber 103 into the second chamber 104, and the combustion-supporting gas that enters the second chamber 104 enters the third chamber 105. Since the flow direction of the combustion-supporting gas in the second chamber 104 is opposite to the flow direction of the combustion-supporting gas in the third chamber 105, that is, the combustion-supporting gas entering the second chamber 104 enters the third chamber 105 again in the opposite flow direction, the reverse rectifying of the combustion-supporting gas by the reverse rectifying portion 1 is realized.
Thus, in the nozzle test device 100 for a combustion chamber of a gas turbine according to the embodiment of the present invention, the reverse rectifying portion 1 is provided to reversely rectify the combustion-supporting gas entering the reverse rectifying portion 1 and then blend the rectified combustion-supporting gas with the fuel ejected from the nozzle 2. The flow uniformity of combustion-supporting gas is improved, the airflow structure at the nozzle 2 is truly simulated, the consistency of the test conditions of the nozzle 2 and the real working environment of the gas turbine is maintained, and the accuracy of the performance test data of the nozzle 2 is further improved, so that the reliability of the nozzle test device 100 for the combustion chamber of the gas turbine is further improved.
Optionally, the reverse rectifying portion 1 further comprises an annular third sealing plate 9, the third sealing plate 9 being blocked at the third port 501, the third sealing plate 9 having an inner bore 901, the inner bore 901 being provided for passing at least a portion of the nozzle 2, such that the third cylinder 6 and the nozzle 2 define the third chamber 105.
For example, the nozzle 2 is provided with a flange, the third sealing plate 9 is provided with a plurality of blind holes, and the flange is connected with the blind holes through bolts, so that the nozzle 2 is fixedly mounted on the third sealing plate 9. The nozzle 2 is pierced with the inner hole 901 of the third sealing plate 9 in the left-right direction, and the nozzle opening of the nozzle 2 is placed in the third cylinder 6 so that the third chamber 105 is formed between the inner peripheral surface of the third cylinder 6 and the outer peripheral surface of the nozzle 2.
Therefore, the third sealing plate 9 is arranged to seal the third port 501, so that the third chamber 105 is defined between the third cylinder 6 and the nozzle 2, and the gas turbine combustor nozzle testing device 100 is simple in structure and reasonable in arrangement.
Optionally, a nozzle testing apparatus 100 for a combustion chamber of a gas turbine according to an embodiment of the present invention further includes an air intake portion 11 and a combustion portion 12. The air intake portion 11 communicates with the first chamber 102, the air intake portion 11 is supplied with combustion-supporting gas, the combustion portion 12 communicates with the third chamber 105 so that the combustion-supporting gas and fuel are mixed and combusted to form high-temperature fuel gas, and the combustion-supporting gas supplied to the third chamber 105 is mixed with fuel ejected from the nozzle 2 and combusted in the combustion portion 12 to form high-temperature fuel gas.
In some embodiments, the reverse rectifying portion 1 further comprises a fourth chamber 106 in communication with the first chamber 102, the fourth chamber 106 being provided upstream of the first chamber 102, the fourth chamber 106 being adapted to communicate with a source of combustion gas, the flow direction of the combustion gas in the fourth chamber 106 intersecting the flow direction of the combustion gas in the first chamber 102.
For example, as shown in fig. 1, combustion-supporting gas of the air inlet portion 11 enters the first chamber 102 through the fourth chamber 106, and the fourth chamber 106 is provided to facilitate communication between the air inlet portion 11 and the first chamber 102, so that the device 100 for testing the nozzle of the combustion chamber of the gas turbine according to the embodiment of the invention has a simple structure and is convenient to connect.
In some embodiments, the reverse rectifying portion 1 further comprises a fifth chamber 107 in communication with the fourth chamber 106, the fifth chamber 107 being provided upstream of the fourth chamber 106, the fifth chamber 107 being adapted to communicate with a source of combustion gas, the flow direction of the combustion gas in the fifth chamber 107 intersecting the flow direction of the combustion gas in the fourth chamber 106.
For example, as shown in fig. 1, the combustion-supporting gas in the air inlet portion 11 enters the fourth chamber 106 through the fifth chamber 107, and by providing the fourth chamber 106 and the fifth chamber 107, the combustion-supporting gas in the air inlet portion 11 further enters the first chamber 102 conveniently, so that the device 100 for testing the nozzle of the combustion chamber of the gas turbine according to the embodiment of the invention has a simple structure and is convenient to connect.
Optionally, the extending direction of the first chamber 102 is perpendicular to the extending direction of the second chamber 104, so that the flow direction of the combustion-supporting gas in the first chamber 102 is perpendicular to the flow direction of the combustion-supporting gas in the second chamber 104.
Optionally, the extending direction of the fourth chamber 106 is perpendicular to the extending direction of the first chamber 102, so that the flow direction of the combustion-supporting gas in the fourth chamber 106 is perpendicular to the flow direction of the combustion-supporting gas in the first chamber 102.
Optionally, the extending direction of the fifth chamber 107 is perpendicular to the extending direction of the fourth chamber 106, so that the flow direction of the combustion-supporting gas in the fifth chamber 107 is perpendicular to the flow direction of the combustion-supporting gas in the fourth chamber 106.
For example, as shown in fig. 1, the extending direction of the first chamber 102 is perpendicular to the extending direction of the second chamber 104, the extending direction of the fourth chamber 106 is perpendicular to the extending direction of the first chamber 102, and the extending direction of the fifth chamber 107 is perpendicular to the extending direction of the fourth chamber 106. The combustion-supporting gas in the air inlet part 11 deflects 90 ° into the fifth chamber 107, the combustion-supporting gas in the fifth chamber 107 deflects 90 ° and then enters the fourth chamber 106, the combustion-supporting gas in the fourth chamber 106 deflects 90 ° and then enters the first chamber 102, and the combustion-supporting gas in the first chamber 102 enters the transition chamber 103 in a side air inlet manner.
Therefore, the first chamber 102, the second chamber 104, the third chamber 105, the fourth chamber 106 and the fifth chamber 107 are reasonably arranged, so that the gas turbine combustion chamber nozzle testing device 100 is simple in structure and reasonable in arrangement.
In some embodiments, a combustion nozzle testing apparatus 100 for a gas turbine combustor of the present invention further includes a combustion gas conduit 10, the combustion gas conduit 10 being disposed upstream of the first chamber 102, the combustion gas conduit 10 including a first tube segment 1001, a second tube segment 1002, and a third tube segment 1003 connected in sequence, the second tube segment 1002 being disposed upstream of the first tube segment 1001, the third tube segment 1003 being disposed upstream of the second tube segment 1002, the first tube segment 1001 defining the first chamber 102, the second tube segment 1002 defining the fourth chamber 106, the third tube segment 1003 defining the fifth chamber 107.
Therefore, the first chamber 102, the fourth chamber 106 and the fifth chamber 107 are respectively formed by the first pipe section 1001, the second pipe section 1002 and the third pipe section 1003 of the combustion-supporting gas pipeline 10, so that the device 100 for testing the nozzle of the combustion chamber of the gas turbine has a simple structure and is convenient to install.
Alternatively, the combustion-supporting gas piping 10 is provided in plural, and the plural combustion-supporting gas piping 10 are arranged at intervals along the circumferential direction of the nozzle mounting portion 101.
As shown in fig. 1 and 3, the combustion-supporting gas piping 10 is provided with four, and the four combustion-supporting gas piping 10 are arranged at regular intervals in the circumferential direction of the nozzle mounting portion 101.
Thus, the combustion-supporting gas of the air inlet part 11 enters the transition chamber 103 through the plurality of combustion-supporting gas pipelines 10, so that the uniformity of annular flow of the combustion-supporting gas in the transition chamber 103 is improved, and the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine is further improved.
Alternatively, the combustion-supporting gas piping 10 is provided in plural, and the plural combustion-supporting gas piping 10 are arranged at intervals along the circumferential direction of the nozzle mounting portion 101.
As shown in fig. 1 and 3, the combustion-supporting gas piping 10 is provided with four, and the four combustion-supporting gas piping 10 are arranged at regular intervals in the circumferential direction of the nozzle mounting portion 101.
Thus, the combustion-supporting gas of the air inlet part 11 enters the transition chamber 103 through the plurality of combustion-supporting gas pipelines 10, so that the uniformity of annular flow of the combustion-supporting gas in the transition chamber 103 is improved, and the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine is further improved.
Alternatively, the air intake portion 11 is an air intake pipe, each of the combustion-supporting gas pipes 10 communicates with the air intake pipe, and a plurality of the combustion-supporting gas pipes 10 are arranged around the center line of the air intake pipe.
By arranging a plurality of combustion-supporting gas pipelines 10 around the center line of the air inlet pipe, the air inlet working condition of each combustion-supporting gas pipeline 10 can be the same, so that the reliability of the nozzle testing device 100 for the combustion chamber of the gas turbine is further improved.
Alternatively, the combustion section 12 is a combustion tube, at least a portion of which extends into the third barrel 6 such that the third chamber 105 communicates with the combustion section 12.
Alternatively, the combustion tube includes a large diameter section 1202 and a small diameter section 1201, the large diameter section 1202 being provided downstream of the small diameter section 1201, the small diameter section 1201 extending into the third cylinder 6.
For example, as shown in fig. 1, the third cylinder 6 is sleeved on the small-diameter section 1201, and the third cylinder 6 communicates with the small-diameter section 1201. The combustion-supporting gas and the fuel sprayed by the nozzle 2 enter the large-diameter section 1202 for combustion after being mixed in the small-diameter section 1201, and high-temperature fuel gas generated by the combustion in the large-diameter section 1202 is discharged through the right port of the large-diameter section 1202.
Thus, by providing the combustion section 12 as the small diameter section 1201 and the large diameter section 1202, the structure is simple, facilitating the mixed combustion gas and fuel in the third cylinder 6 to enter the combustion section 12 for combustion.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, or communicable with each other, directly connected, indirectly connected through an intervening medium, or in communication between two elements or in an interactive relationship between two elements, unless otherwise explicitly specified. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.
Claims (14)
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| CN115506917B (en) * | 2022-10-27 | 2025-04-22 | 清航空天(北京)科技有限公司 | A continuous rotating detonation engine |
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| US20160186663A1 (en) * | 2014-12-30 | 2016-06-30 | General Electric Company | Pilot nozzle in gas turbine combustor |
| CN104880320B (en) * | 2015-06-19 | 2017-05-24 | 中国人民解放军装备学院 | Evaluation device and evaluation method for nozzle stability |
| JP6599738B2 (en) * | 2015-11-25 | 2019-10-30 | アイシン精機株式会社 | Intake device for internal combustion engine |
| US20170248318A1 (en) * | 2016-02-26 | 2017-08-31 | General Electric Company | Pilot nozzles in gas turbine combustors |
| CN107014618B (en) * | 2017-03-29 | 2019-03-29 | 浙江大学 | An experimental research device for the coupling mechanism of combustion chamber and turbine |
| CN108918117A (en) * | 2018-07-02 | 2018-11-30 | 武汉三江航天远方科技有限公司 | Heavy oil burner jet combustion performance testing device and its test method |
| CN110763474B (en) * | 2018-07-25 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
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