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CN101592084A - The low noise ejector that is used for turbo machine - Google Patents

The low noise ejector that is used for turbo machine Download PDF

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Publication number
CN101592084A
CN101592084A CNA2009101459076A CN200910145907A CN101592084A CN 101592084 A CN101592084 A CN 101592084A CN A2009101459076 A CNA2009101459076 A CN A2009101459076A CN 200910145907 A CN200910145907 A CN 200910145907A CN 101592084 A CN101592084 A CN 101592084A
Authority
CN
China
Prior art keywords
nozzle
end portion
arrangement
turbo machine
size
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
Application number
CNA2009101459076A
Other languages
Chinese (zh)
Inventor
C·G·肖特
K·W·金滋
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN101592084A publication Critical patent/CN101592084A/en
Pending legal-status Critical Current

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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
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present invention relates to be used for the low noise ejector of turbo machine, particularly, a kind of turbo machine (2) comprises compressor (4) and sparger (55).This sparger comprises that at least one has the nozzle of first end portion (70) (60), and this first end portion (70) is extended to second end portion (71) that limits flow region (75).Second end portion (71) comprises the variable outlet (78) that is used for controlling from the air-flow of compressor (4).

Description

The low noise ejector that is used for turbo machine
Technical field
The present invention relates to the sparger technology, more specifically, relate to the low noise ejector that is used for turbo machine.
Background technique
At least some known spargers mix two kinds of streams that flow, and high pressure main flow or starting stream (motive stream) and low pressure time stream or suction stream have the more discharge currents of low-pressure of intermediate pressure or two inlet flows of ratio with generation.Injector nozzle promotes this mixed process by the high pressure starting stream that quickens the generation high-speed jet.High-speed jet was led mixing tube or mixing chamber to take away the low pressure suction stream.Then, these two kinds of mixed flows are typically discharged by diffuser.
Will the throttling of starting stream so that sparger output with non-design (calculated) load and/or the turbine coupling under environmental conditions, moved.Because output is reduced, existing throttling arrangement keeps constant high-speed jet diameter.In this device, reduce flow by the effective velocity that reduces starting stream.Stoped carry secretly (entrainment) of sparger in the descend speed of low starting stream of throttling condition, thereby limited whole throttling range and reduced and carried performance secretly.
Summary of the invention
According to one exemplary embodiment of the present invention, turbo machine comprises compressor and sparger.This sparger comprises that at least one has the nozzle of first end portion, and this first end portion extends to second end portion that limits flow region.Second end portion comprises the variable outlet that is used to control from the air-flow of compressor.
According to another exemplary embodiment of the present invention, the sparger that is used for turbo machine comprises that at least one has the nozzle of first end portion, and this first end portion extends to second end portion that limits flow region.This second end portion comprises the variable outlet that is configured to control from the air-flow of compressor.
According to another exemplary embodiment of the present invention, control comprises by the method for the air-flow of turbo machine sparger: the compressor section at turbo machine produces air-flow; Guide air-flow into sparger; Air-flow is reached the nozzle of sparger; And make air communication cross the variable exit portion of nozzle.
Technology by exemplary embodiment of the present realizes additional feature and advantage.Other embodiments of the invention and aspect obtain describing in detail in this article, and are considered to the part of desired invention.In order to understand advantages and features of the invention better, but reference implementation mode and accompanying drawing.
Description of drawings
Fig. 1 is that this low noise ejector comprises the nozzle with selectively variable hole according to the schematic representation of the gas turbine engine with low noise ejector of one exemplary embodiment of the present invention;
Fig. 2 is the partial schematic diagram according to the nozzle with selectively variable hole of one exemplary embodiment of the present invention, and it illustrates the selectively variable hole that is first configuration;
Fig. 3 is the partial schematic diagram of the nozzle among Fig. 2, and it illustrates the selectively variable hole that is second configuration;
Fig. 4 is the partial schematic diagram according to the nozzle with selectively variable hole of another exemplary embodiment of the present invention, and it illustrates the selectively variable hole that is first configuration; And
Fig. 5 is the partial schematic diagram of the nozzle among Fig. 4, and it illustrates the selectively variable hole that is second configuration.
List of parts:
2 Gas turbine engine
4 Compressor
6 Compressor stage
7 Compressor stage
8 Compressor stage
9 Compressor stage
12 Turbine
14 Axle
17 Turbine stage
18 Turbine stage
19 Turbine stage
30 Cooling system
41 First cooling circuit
44 Second cooling circuit
47 Bypass circulation
48 Bypass valve
55 Sparger
58 The connector loop
60 Nozzle
70 First end portion (60)
71 Second end portion (60)
72 Intermediate portion (60)
75 Flow region
78 Variable outlet
79 The V-arrangement arm
82 Exit orifice
88 Pilot jet
91 Actuator shaft
93 Strut
97 First end (88)
98 Second end (88)
99 Intermediate portion (88)
104 Auxiliary V-arrangement arm
107 Pilot outlet/hole
120 Nozzle
124 The starting pipe
128 First end portion (124)
129 Second end portion (124)
130 Intermediate portion (124)
132 Flow region
133 Variable outlet
136 The V-arrangement arm
138 First end portion (136)
139 Second end portion (136)
140 Intermediate portion (136)
142 Hinge
154 The V-arrangement armlet
157 First end (154)
158 Second end (154)
161 Actuator rod
165 The hole
166 First size
169 Second size
Embodiment
At first with reference to figure 1, the turbo machine with shown in the form of gas turbine engine of constructing according to one exemplary embodiment of the present invention usually is denoted as 2.Turbogenerator 2 comprises compressor 4, and this compressor 4 has a plurality of compressor stages, and four compressor stages wherein indicate with 6 to 9.Compressor 4 operationally is connected on the turbine 12 via axle 14.Turbine 12 comprises a plurality of turbine stage, and three turbine stage wherein indicate with 17 to 19.Turbine 12 also comprises and will guide the cooling system 30 of turbine 12 into from the cooling blast of compressor 4.In other words, cooling air is sucking-off in not at the same level 9 from level 6 to level, and the corresponding stage of the level 17 of passing to turbine 12 to the level 19.
For this purpose, cooling system 30 comprises first cooling circuit 40 that compressor stage 7 and turbine stage 19 are interconnected.In the illustrated embodiment, compressor stage 7 is medium pressure grades, and it is connected to the corresponding medium pressure grade 19 of turbine 12.Cooling system 30 also comprises second cooling circuit 44 that compressor stage 8 and turbine stage 18 are interconnected.Compressor stage 8 is in the pressure higher than level 7, and thereby be connected on the level 18, this grade 18 similarly is in the pressure higher than level 17.In addition, cooling system 30 is depicted as and comprises that the bypass circulation 47 with bypass valve 48, this bypass circulation optionally move to keep the internal pressure in the turbogenerator 2.
In order to use the high-pressure air from compressor 4 as few as possible, second cooling circuit 44 has sparger 55, and this sparger is operably connected on first cooling circuit 40 through connector loop 58.By this layout, the high pressure main air flow by sparger 55 or play moving air flow and suck from the low pressure secondary air of first cooling circuit 40 or the part of suction stream.High pressure draught and low-pressure air current mix to form combined airflow, main nozzle or the pilot jet 60 of this combined airflow guiding by being positioned at sparger 55.Pilot jet 60 with the high-pressure liquid speedup to more speed so that substantially with turbine stage for example 18 in hydrodynamic pressure and speeds match.Yet, when changing in the whole operation scope of the pressure in the turbine stage 18 at turbine 12, as being described in a more detailed discussion below, sparger 55 is optionally regulated to control the pressure in second cooling circuit 44, so that mate the pressure in the turbine stage 18 in the wide operating range of turbine 12.
Referring now to Fig. 2 and Fig. 3, the pilot jet 60 according to first exemplary embodiment structure of the present invention is described.As shown in the figure, pilot jet 60 comprises first end portion 70, and this first end portion 70 extends to second end portion 71 by the intermediate portion 72 that limits flow region 75.As below will do discussed in detail, second end portion 71 comprises variable outlet 78.According to this exemplary embodiment, variable outlet 78 is partly limited by the V-arrangement arm 79 (chevron) that is arranged in second end portion, 71 places.V-arrangement arm 79 is designed to reduce the overall noise from sparger 55.In order to control air-flow, V-arrangement arm 79 is configured to extend to the center line of sparger 55 (not indicating separately).V-arrangement arm 79 is defined for the first size 85 of variable outlet 78.
Further according to shown in this exemplary embodiment, sparger 55 comprises the auxiliary starter nozzle 88 that is installed in the pilot jet 60.Auxiliary starter nozzle 88 is operably connected on the actuator shaft 91 by a plurality of struts (one of them is denoted as 93).As following discussed in detail, actuator shaft 91 is optionally operated, so as in flow region 75 mobile auxiliary starter nozzle 88, thereby control is from the whole output of sparger 55.For this purpose, auxiliary starter nozzle 88 comprises first end portion 97 of extending to second end portion 98 by intermediate portion 99.Intermediate portion 99 limits auxiliary V-arrangement arm 104, and it correspondingly is defined for second size of variable outlet 78.
By this layout, at the basic load run duration of turbine 2, auxiliary starter nozzle 88 is converted to first configuration as shown in Figure 2, and wherein, the air that passes flow region 75 passes the variable outlet 78 that is configured in first size 85 places.Yet, departing from the basic load run duration or when ambient air temperature is outside design parameter, auxiliary starter nozzle 88 is to second configuration conversion shown in Figure 3, and wherein, the air-flow that flows through flow region 75 is conducted through the variable outlet 78 that is configured in second size, 107 places.More specifically, in second configuration shown in Figure 3, auxiliary V-arrangement arm 104 is in abutting connection with the V-arrangement arm 79 of closing or dwindle variable outlet 78.Certainly, according to specific motion speed and/or ambient air conditions, auxiliary starter nozzle 88 can be transferred to any one in the (not shown) of a plurality of neutral positions, so that set up any amount of intermediate sizes that is used for variable outlet 78, producing desirable stream pressure/speed, thereby cooling air is offered turbine stage 18.By this layout, sparger 55 optionally is configured to produce the pressure/capacity of wide range, thereby in the wide range of operation of crossing over turbine 2, with the operating pressure coupling in the turbine stage.
With reference now to Fig. 4 and Fig. 5,, the pilot jet 120 of another exemplary embodiment structure according to the present invention is described.As shown in the figure, nozzle 120 comprises starting pipe 124, and this pipe has first end portion 128 of extending to second end portion 129 by intermediate portion 130, so that limit flow region 132.To be similar to mode as described above, second end portion 129 comprises variable outlet 132.Nozzle 120 further comprises a plurality of V-arrangement arms (one of them is denoted as 136), and as hereinafter discussed in detail, the V-arrangement arm is defined for the outlet geometrical shape and the size of variable outlet 132.Also to be similar to mode as described above, V-arrangement arm 136 extends to the center line (not indicating separately) of sparger 55, so that the output of chien shih noise minimizes in the turbine runtime.In the illustrated embodiment, each V-arrangement arm 136 comprises first end portion 138 of extending to second end portion 139 by intermediate portion 140.According to shown in this exemplary implementation column, each V-arrangement arm 136 is pivotally mounted on the starting pipe 124, thereby comprises hinge 142.As below being described in greater detail, V-arrangement arm 136 optionally pivots between the primary importance (shown in Figure 4) and the second place (shown in Figure 5).
In order to control the selectivity motion of V-arrangement arm 136, nozzle 120 has the V-arrangement armlet 154 that is installed to slidably on the starting pipe 124.V-arrangement armlet 154 comprises first end 157 that extends to second end 158.Second end 158 is operably connected on first end portion 138 of a plurality of V-arrangement arms 136.First end portion 157 is operably connected on the actuator rod 161, and actuator rod 161 optionally moves, so that between the primary importance shown in Figure 4 and the second place shown in Figure 5 V-arrangement arm 136 is moved or locate.
At the normal or basic load run duration of turbine 2, actuator rod 161 moves so that cause V-arrangement armlet 154 that V-arrangement arm 136 is moved to the illustrated foundation of Fig. 4 has the exit portion of first size 166 or first configuration in hole 165.By this way, enough air-flow passes flow region 132 and enters compressor stage 18.Departing from the basic load run duration, or when ambient temperature was outside design parameter, actuator rod 161 reacted on V-arrangement armlet 154, to close the V-arrangement arm 136 that hole 165 is gone to second size 169 littler than first size 166.By this way, the cooling air of capacity and sufficient temp is passed to turbine stage 18, departs from the basic load operation so that regulate.
In this, will be appreciated that sparger 55 provides the air-flow output of selectively variable, thereby make the mobile interior pressure condition of turbine part that can be adjusted to the turbogenerator of crossing over wide range of operation of cooling circuit.That is to say, sparger is more adjustable under wideer scope or operating conditions according to an exemplary embodiment of the present invention, so that provide more controls under hotter temperature, and provides additional adjustment to provide cooling air in crossing over wideer range of operation.Also will be appreciated that and to use multiple different structure to form variable outlet.
Generally speaking, this written description usage example comes open the present invention, comprises optimal mode, and also makes those skilled in the art can put into practice the present invention, comprises the method for making and using any device or system and carry out any combination.Claim of the present invention is defined by the claims, and can comprise other example that those skilled in the art expect.If other example has not different with the literal expression of claim structure important documents, do not have the different equivalent structure important document of essence if perhaps other example comprises with the literal expression of claim, then this other example is in the scope of exemplary embodiment of the present.

Claims (7)

1. a turbo machine (2) comprising:
Compressor (4); And
Be connected to the sparger on this compressor (4) fluid, this sparger (55) comprises at least one nozzle (60) with first end portion (70), this first end portion (70) is extended to second end portion (71) that limits flow region (75), and this second end portion (71) comprises the variable outlet (78 that is used for controlling from the air-flow of this compressor (4); 133).
2. turbo machine according to claim 1 (2) is characterized in that, described at least one nozzle (60) comprises first nozzle (60) and second nozzle (88), and described second nozzle is arranged with described first nozzle (60) slidably.
3. turbine according to claim 2 (2) is characterized in that, described first nozzle (60) comprises first V-shaped part (79) of the first size that is defined for described variable outlet (78); And described second nozzle (88) comprises second V-shaped part (104) of second size that is defined for described variable outlet (78); Described second size is different from described first size; Described second nozzle (88) can move between the primary importance and the second place; In primary importance, pass this variable outlet (78) that is configured in first size from the air-flow of described compressor (4), in the second place, pass the variable outlet that is configured in second size from the air-flow of compressor.
4. turbo machine according to claim 1 (2), it is characterized in that, described variable outlet (133) is limited by a plurality of V-arrangement arms (79), and each V-arrangement arm in a plurality of V-arrangement arms (136) is pivotally connected on second end (71) of described at least one nozzle (60).
5. turbo machine according to claim 4 (2) is characterized in that, described turbo machine also comprises: be operably connected to the V-arrangement armlet (154) on each V-arrangement arm in a plurality of V-arrangement arms (136).
6. turbo machine according to claim 5 (2) is characterized in that, described V-arrangement armlet (154) is installed at least one nozzle (120) movably.
7. turbo machine according to claim 4 (2), it is characterized in that, described turbo machine also comprises: be operably connected to the actuator rod (161) on the V-arrangement armlet (154), this actuator rod (161) is suitable for optionally making V-arrangement armlet (154) to move between the primary importance and the second place, in primary importance, variable outlet (133) is with the first size configuration, in the second place, variable outlet (133) is with second dimensional configurations, and described second size is different from described first size.
CNA2009101459076A 2008-05-29 2009-05-31 The low noise ejector that is used for turbo machine Pending CN101592084A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/129,280 US20090297339A1 (en) 2008-05-29 2008-05-29 Low noise ejector for a turbomachine
US12/129280 2008-05-29

Publications (1)

Publication Number Publication Date
CN101592084A true CN101592084A (en) 2009-12-02

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CNA2009101459076A Pending CN101592084A (en) 2008-05-29 2009-05-31 The low noise ejector that is used for turbo machine

Country Status (5)

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US (1) US20090297339A1 (en)
JP (1) JP5663144B2 (en)
CN (1) CN101592084A (en)
DE (1) DE102009025813A1 (en)
FR (1) FR2931884A1 (en)

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Publication number Publication date
JP5663144B2 (en) 2015-02-04
US20090297339A1 (en) 2009-12-03
JP2009287557A (en) 2009-12-10
DE102009025813A1 (en) 2009-12-03
FR2931884A1 (en) 2009-12-04

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Application publication date: 20091202