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WO2013064293A1 - Turbine à gaz et procédé permettant l'injection de combustible - Google Patents

Turbine à gaz et procédé permettant l'injection de combustible Download PDF

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Publication number
WO2013064293A1
WO2013064293A1 PCT/EP2012/067367 EP2012067367W WO2013064293A1 WO 2013064293 A1 WO2013064293 A1 WO 2013064293A1 EP 2012067367 W EP2012067367 W EP 2012067367W WO 2013064293 A1 WO2013064293 A1 WO 2013064293A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
gas turbine
stages
stage
swirl
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.)
Ceased
Application number
PCT/EP2012/067367
Other languages
German (de)
English (en)
Inventor
Werner Krebs
Christian Beck
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of WO2013064293A1 publication Critical patent/WO2013064293A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • Gas turbine and method for injecting fuel The invention relates to a gas turbine and a method for injecting fuel.
  • thermoacoustic instabilities Furthermore occur in gas turbine combustors at certain operating points on thermoacoustic instabilities.
  • Instabilities are largely determined by the axial heat release distribution, the convective time scale of the premix system, and the convective time scale of the flame.
  • the so-called convective time scale can be seen as a quotient between the convective potential
  • the axial heat release distribution and the convective timescale of the flame are also affected by the global reac ⁇ tion rate. Furthermore, it is generally found that too high an overall rate of reaction generated a high heat setting free ⁇ density, which can lead to thermoplastic acoustically induced combustion instabilities.
  • the global reaction rate is influenced by chemistry and turbulence.
  • High turbulence of the flow in the region of the flame folds the flame, thus increasing the flame ⁇ surface, thereby increasing the overall reaction rate.
  • Imposing a circumferential component on the flow, which can also be called a spin, can, like turbulence, fold the flame and thus increase the global reaction rate.
  • Burners which can burn both natural gas and synthesis gas or hydrogen, have hitherto been designed as diffusion burners, in which the fuel and the combustion air are supplied to the combustion chamber via separate passages.
  • the invention is directed to a gas turbine having a burner assembly with at least ei ⁇ NEM Brennstoffinj ector, a flow direction and a burner assembly arranged downstream of the combustion chamber, wherein the Brennstoffinj ector is arranged at an angle to the flow direction, so that the injected fuel imprinting a spin on the flow. If the swirl is not impressed as usual by a swirl lattice, but according to the invention by a suitable fuel injector injector generated, the intensity of the swirl can be influenced from the outside.
  • the momentum of the air flow it is not usual to use the momentum of the air flow, but rather the momentum of the fuel to produce swirl.
  • This allows a load-dependent (ie dependent on the performance of the gas turbine) control of the swirl or the peripheral component of the flow, compared to previous arrangements in which the swirl is generated by flow guide Umble completely constant over the Lastbe ⁇ rich the gas turbine.
  • a flexible combustion system that can change varia ⁇ bel or load-dependent global reaction rate. At partial load an increase in the reaction rate is set ⁇ , while at base load of the machine, a lower global reaction rate is advantageous and can be adjusted.
  • the burner assembly has two stages of fuel injectors that differ in nozzle orientation to provide controllability of angular momentum transfer
  • One stage may have at least one radial and / or axial fuel injector and the other stage may have at least one tangential fuel injector.
  • the swirl number can be adjusted continuously. This allows egg ⁇ ne significant change burner essential parameters in the operation, thus allowing the use of the gas turbine in a wide operating range.
  • the two stages of the burner assembly can be designed so that the fuel ertei ⁇ ment is not significantly changed by a change in the application of the two stages. It is conceivable aller- now also to selectively set with the two stages is dependent on the Beauf ⁇ suppression of radial fuel distribution. This can also have a significant influence on the properties of the flame.
  • the other step may be disposed in relation to the one stage radial au ⁇ hod. Thus, a good mixing of the fuel-air mixture and a good generation of the twist can be realized.
  • the two stages of the burner assembly may have a different axial position, for example in the premix. Thus, a change in the loading of the two stages also has an effect on the mean convective time scale of the premix.
  • Two burner arrangements can be provided spaced apart in the flow direction. With this configuration, the twist and the convective timescale of Vormischstre ⁇ blocks can be varied separately.
  • the gas turbine may include a mechanical swirl generator, such as a swirl grid or baffles, to increase the level of swirl.
  • a mechanical swirl generator such as a swirl grid or baffles
  • the burner arrangement then allows an adaptation of the swirl number of a spin-stabilized flame. So can be set by the or the swirl generators, a certain proportion of the basic twist, currency rend over the Brennstoffinj ector, or the application of fuel, a further variable portion of the swirl is a ⁇ adjustable.
  • the arrangement of fuel injectors and / or stages may be different for different fuels.
  • the invention proposes the use of the fuel injection for influencing the swirl intensity of the fuel-air mixture.
  • the volume flow for ⁇ What serstoffreiche gases is greater by a factor of 2 to 5 as the flow rate of natural gas. This can be a set under ⁇ Kunststoffaji twist, resulting in a different flame front density for different fuels with different reactivity.
  • the combustion air is aerodynamically - slightly twisted by baffles or tangential injection. That is, in addition to the axial component, it has a tangential component, wherein the tangential component can be between 5% and 40% of the axial component.
  • Fuel can now be injected by the arrangement of Brennstoffinj ectors and / or the stages with a different injection angle.
  • Synthesis gas or water ⁇ material can be added either contrary to the spin direction of the air flow or with a corresponding larger proportion against the swirl direction of the air flow. This results in a change in the swirl component with a change in the fuel.
  • the invention is directed to a method of injecting fuel into a gas turbine with egg ⁇ ner burner assembly is directed, wherein the directed by injection of fuel through two stages of Brennstoffin- jectors a swirl in the fuel-air mixture is generated and the swirl number is continuously adjusted by changing the application of the two stages.
  • the moving ⁇ chen advantages and modifications will apply as described above.
  • fuel may be injected radially and / or axially, and in another stage of the burner assembly, fuel may be tangentially injected.
  • the swirl number can be adjusted steplessly that by changing the impingement of the two stages, enabling light ⁇ a significant change essential burner Para ⁇ meter in operation, thus allowing the use of the gas turbine in a wide operating range.
  • the two stages of the burner assembly can be designed so that the fuel distribution by a change in the application of the two stages is not essential. It is also conceivable, however, to set a radial fuel distribution that is dependent on the application with the two stages. This can also have a significant influence on the properties of the flame.
  • FIG. 1 shows a first example of a burner arrangement of a gas turbine.
  • FIG. 2 shows a second example of a burner arrangement.
  • Figure 3 shows a section along the line III-III in
  • FIG. 4 shows a third example of a burner arrangement.
  • FIG. 5 shows a double burner arrangement.
  • FIG. 6 shows an example of a burner arrangement
  • FIG. 7 shows a front view of a burner arrangement with pilot burner.
  • Figure 8 shows a further example of a Brenneranord ⁇ voltage with swirl generator.
  • Figure 9 shows yet another example of a burner ⁇ arrangement with swirl generator.
  • Figure 10 shows yet another example of a burner ⁇ arrangement with swirl generator.
  • FIG. 11 shows a swirl generator
  • FIG. 12 shows a change in the angular momentum flow of the air flow with one-sided injection of synthesis gas.
  • a premix 4 is arranged downstream of the arrangement 2, to which a combustion chamber 5 adjoins further downstream.
  • the flow direction S may be the main flow direction in the case of a twisted or turbulent flow.
  • a plurality of burner assemblies 3 are preferably arranged concentrically to a rotation axis or axis of symmetry R. Accordingly, the direction of flow S may be based on the whole gas turbine 1 or egg ⁇ ne single burner assembly.
  • one or more air inlets 6 are provided, so that a fuel-air mixture is formed in the premix 4, which is located in the combustion chamber 5 ignited and burned in a flame 7.
  • Gas turbines without premixing can also be used.
  • the one or more fuel injectors 3 are arranged at an angle to the flow direction S, so that they impress a twist on the fuel-air mixture.
  • the spin then folds the flame 7, increasing the global response rate.
  • the gas turbine can work at partial load in an optimal Be ⁇ operating point.
  • the burner assembly 2 has two stages 8 and 9 of Brennstoffinj ectors 3.
  • the two stages are arranged concentrically, with a first stage 8 is arranged centrally and a second stage 9, the first stage 8 circumferentially surrounds or is arranged radially outboard.
  • steps in the axial direction i. arranged in the flow direction S at about the same height.
  • Each stage has a fuel supply and / or a fuel distributor, with which the fuel to the individual
  • Fuel injectors 3 passes or is distributed to them.
  • the first stage 8 is disposed on an axially extending tube, such as a central fuel lance, or comprises the tube.
  • the first stage 8 includes radial fuel bores, nozzles or fuel injectors 3a.
  • the radial fuel injectors 3a are arranged in the region of the downstream end of the tube and can be arranged on an outer peripheral surface of the tube and / or on a conical surface of a tube tip. Over the circumference several fuel injectors 3a are distributed, for example four or eight.
  • the second stage 9 is designed as an annular fuel distributor with tangential fuel bores, nozzles or fuel injectors 3b. Tangential alignment means that the openings of the fuel injectors 3b are included in the drawing. level and / or oriented out of the plane of the drawing.
  • 2 shows another embodiment of a gas turbine 1 with burner assembly 2 is shown in the existing designs in particular ⁇ sondere a DOC (Depleted Oxygen combustion) gas turbine can presumably be more easily integrated. While the structure of the gas turbine 1 is identical to that shown in FIG. 1, the burner assemblies 2 are different from each other.
  • the burner assembly 2 also has a first stage 8, which is tubular or is arranged on a tube and the ra ⁇ Dialen Brennstoffinj comprises reflectors 3a, which are arranged at a harshest operating peripheral surface of the tube.
  • the tube be ⁇ there is an inner tube, which is preferably sealed off from a downstream end side of the tube exits ⁇ and serves as a fuel supply line for the second stage.
  • the fuel for the first stage 8 is passed through the pipe separately from the second stage feed 9.
  • the fuels for both stages 8 and 9 may be identical or different.
  • the two stages 8 and 9 can be activated individually or jointly. Also, the admission, that is, the amount of fuel per unit time or the fuel pressure, the two stages may be identical or different.
  • the second stage 9 has a multi-arm fuel distributor or fuel injectors with several, here four examples, tangential Brennstoffinj injectors 3b.
  • FIG. 3 shows a plan view of the second stage 9 according to section III-III in FIG. Each fuel injector 3b is disposed in an arm of the second stage 9.
  • FIG. 4 shows a further embodiment of a gas turbine 1 with burner arrangement 2.
  • the structure of the gas turbine 1 is identical or similar to the previous embodiments.
  • the burner assembly 2 in turn has two stages 8 and 9, the first stage 8 comprising an axial fuel injector 3c disposed at a downstream end of an inner tube. It can also have several axial fuel injector 3c disposed at a downstream end of an inner tube. It can also have several axial fuel injector 3c disposed at a downstream end of an inner tube. It can also have several axial fuel injector 3c disposed at a downstream end of an inner tube. It can also have several axial
  • Fuel injectors 3c be provided, which are arranged in the front side and / or arms.
  • the stage 9 is arranged on a tube surrounding the inner tube and has a plurality of tangential Brennstoffinj injectors 3b, which are arranged on arms similar to FIG.
  • a change in the actuation of the two stages 8 and 9 affects in this example as well ⁇ the swirl number and the radial mixing profile. Influencing the mixture profile is also achievable with the other variants with a suitable design of the fuel injectors.
  • FIG. 5 shows a further variant of a gas turbine, in which two burner arrangements 2 are provided spaced apart in the flow direction S.
  • the upstream burner assembly 2 has a first stage 8 with radial fuel injectors 3a arranged in a tube.
  • the radial fuel injectors 3a are surrounded by tangential fuel injectors 3b of a second stage 9, wherein both types of nozzles or injectors are located substantially or substantially at an axial height or position.
  • an air inlet 6 is again provided.
  • the downstream second burner assembly 2 has a second stage 9, which is identical or approximately identical to the second stage 9 of the first burner assembly 2 is formed.
  • the first stage 8 of the second burner assembly 2 consists of an inner tube or is arranged on this.
  • the inner tube extends upstream in the tube, emerges from a downstream end of the tube and then proceeds in the premix 4 further to the second burner assembly 2.
  • the radial Brennstoffinj sectors 3a are arranged. These are slightly downstream to the tangential ones
  • Brennstoffinj injectors 3b of the second stage 9 of the second burner assembly 2 are arranged to compensate for the smaller cross-section of the inner tube compared to the tube or the greater distance between the two stages. An arrangement at the same axial height is also possible.
  • the convective time scale of the premix can be adjusted.
  • the quality of mixing is also at least implicitly influenced.
  • the swirl number can be varied independently of the convective time scale.
  • FIG. 6 shows another example of a gas turbine 1 with a burner arrangement 2.
  • the two stages 8 and 9 of the burner arrangement 2 were arranged exactly or substantially at an axial height, the two stages 8 and 9 are the burner arrangement 2 now axially spaced ie arranged in the flow direction S one behind the other or offset.
  • the first stage 8 with radial fuel injectors or nozzles 3a is arranged upstream of a swirl generator 10, for example in the form of a swirl lattice. Downstream of the swirl lattice 10, the second stage 9 is arranged with tangential Brennstoffinj ectors 3b.
  • This spin-stabilized burner arrangement 2 allows a moderate influence on the swirl number.
  • Figure 7 shows an illustration of a front side of the Gasturbi ⁇ ne 1 and an interior space of the gas turbine 1. From the burner arrangement ⁇ 2 are axial Brennstoffinj ectors 3c which are arranged concentrically around a pilot burner. 11 The pilot burner 11 may be the same design as the
  • Brennstoffinj ectors or nozzles 3 have, alternatively, it may have a different design.
  • 8 shows another example of a gas turbine 1 with burner assembly 2 and the swirl generator 10.
  • the burner assembly 2 is positioned upstream of the swirl generator 10, which may the fuel-air mixture with a tangential component shipping ⁇ hen arranged.
  • the one or Fuels for the two stages 8 and 9 are fed centrally and in front of the Drallge ⁇ erator 10 of Brennstoffinj reflectors 3 of the two stages 8 and 9 was added in the passage.
  • Different fuels can be supplied to the two or more stages.
  • the injection of the fuels takes place at an angle to the flow direction S, preferably at an angle between 20 ° to 90 °, wherein an angle of 90 ° means that the fuel is perpendicular to the flow ⁇ direction S or main flow.
  • the injection can take place radially and / or tangentially.
  • Either all the nozzles or fuel injectors 3 of a stage can have an identical orientation, ie radial or tangential, or the fuel injectors 3 of a stage have different orientations.
  • the Brennstoffinj reflectors 3 of the two stages may be the same, or different mixed, that is, a step is aligned radially and axially a step is rich ⁇ tet, oriented or arranged to be.
  • Fuels, such as natural gas and synthesis gas can Müs ⁇ sen but not be different.
  • the injection of synthesis gas takes place only in one direction to the flow direction, whereby a twist is impressed.
  • the injection of natural gas can take place on one side or preferably on both sides . In unilateral injection of an additional will likely generate swirl, while at bilateral or Deltage ⁇ translated injection is no change of the twist.
  • the burner arrangement 2 of the gas turbine 1 is arranged downstream of the swirl generator 10.
  • the burner assembly 2 has only one stage 8 with Brennstoffinj sectors 3.
  • the fuel injectors 3 are arranged at an angle to the flow direction S or inject the fuel at an angle.
  • tangential fuel injectors 3 are used.
  • FIG. 10 shows a further example of a gas turbine 1 with burner arrangement 2 and swirl generator 10.
  • the fuel is injected upstream of the swirl generator 10.
  • a swirl generator 10 an axial blade grid is used.
  • the first stage 8 has radial fuel injectors 3a, which are connected to a separate supply line for fuel.
  • the second stage 9 has tangential Brennstoffinj injectors 3b, which are connected to another separate supply line for fuel.
  • the two supply lines may be formed as concentric tubes in the central region of the premix 4.
  • the first stage 8 is arranged upstream of the second stage 9.
  • a gas or both combustion ⁇ fuel lines or steps may be used.
  • both stages may be used for injection.
  • the number of fuel lines per burner assembly 2 is not limited to two lines, it can also be used a larger number.
  • FIG. 11 shows a development of the stages 8, 9 or of the swirl generator 10.
  • the swirl generator 10 may comprise the two stages, or in other words, the two stages may preferably be in a straight passage of the
  • Twist generator 10 may be provided.
  • the downstream passage is adjoined downstream by a swirl passage with an oblique or bent part, in which the flow deflection of the swirl generator 10 takes place.
  • the natural gas injection stage 8 is located upstream of the syngas injection stage 9.
  • the stage 8 or the upstream end of the swirl generator 10 or the Brenneranord ⁇ tion 2 is just flown by the air.
  • the stage 8 has fuel injectors 3, which are oriented in two opposite directions, so that during the injection of natural gas or gas from this stage 8 no swirl arises or pick up swirl components.
  • the stage 9 has fuel injectors 3, which are oriented in one direction, so that during the injection of synthesis gas or in the case of gas from this stage 9, a twist is created.
  • the angular momentum of the flow is changed by the injection of fuel and by the deflection in the swirl generator 10. This change is shown schematically in FIG. 12 by a triangle of the angular momentum currents.
  • the angular momentum current is defined as:
  • the circumferential velocity component is denoted by ⁇
  • the axial velocity component is denoted by u.
  • the angular momentum of the current airflows mung by the bilateral injection of natural gas is not geän ⁇ changed. Due to the one-sided injection of the synthesis gas (SG) current, however, the angular momentum current is changed, resulting in a Change in the Ausströmwinkels ß res results. Can be above ⁇ attributed by the angular momentum of current for the synthesis gas operation compared to the natural gas can be lowered.
  • the fuel injectors can be arranged centrally, centrally or in the outer region (in the radial direction). For example, a radial injection may be radially outward and / or radially inward.
  • the directional injection of the fuel generates a swirl in the fuel-air mixture. This is done in response to the application of fuel and the operating condition of the gas turbine 1.
  • the twist in depen ⁇ dependence of the load is changed.
  • fuel radi al ⁇ and / or is axially injected while in a further stage 9 of the burner assembly 2, fuel is injected tangentially. This allows a better controllability of the twist and the operating point of the gas turbine.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne une turbine à gaz avec un système de brûleur (2) à deux niveaux (8, 9) d'injecteurs de combustible (3), un sens de flux (S) et une chambre de combustion (5) disposée en aval du système de brûleur (2) ; les deux niveaux (8, 9) d'injecteurs de combustible (3) étant disposés selon un angle par rapport au sens du flux (S), de telle sorte que le combustible injecté provoque un tourbillon sur le flux. Un niveau (8) comprend au moins un injecteur de combustible radial (3a) et/ou axial (3c) et l'autre niveau (9) comprend au moins un injecteur de combustible tangentiel (3b), de telle sorte que le nombre de tourbillons peut être adapté en continu en modifiant l'injection des deux niveaux (8, 9).
PCT/EP2012/067367 2011-11-03 2012-09-06 Turbine à gaz et procédé permettant l'injection de combustible Ceased WO2013064293A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11187643.9 2011-11-03
EP11187643.9A EP2589876A1 (fr) 2011-11-03 2011-11-03 Turbine à gaz et procédé d'injection de carburant

Publications (1)

Publication Number Publication Date
WO2013064293A1 true WO2013064293A1 (fr) 2013-05-10

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WO (1) WO2013064293A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114659137A (zh) * 2022-03-14 2022-06-24 中国航空发动机研究院 一种旋流器和动力装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20250189132A1 (en) * 2023-12-08 2025-06-12 General Electric Company Turbine engine having a combustion section with a fuel nozzle

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100170255A1 (en) * 2009-01-07 2010-07-08 Baifang Zuo Methods and systems to enhance flame holding in a gas turbine engine
US20100300109A1 (en) * 2007-12-19 2010-12-02 Alstom Technology Ltd Fuel injection method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100300109A1 (en) * 2007-12-19 2010-12-02 Alstom Technology Ltd Fuel injection method
US20100170255A1 (en) * 2009-01-07 2010-07-08 Baifang Zuo Methods and systems to enhance flame holding in a gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114659137A (zh) * 2022-03-14 2022-06-24 中国航空发动机研究院 一种旋流器和动力装置
CN114659137B (zh) * 2022-03-14 2023-05-23 中国航空发动机研究院 一种旋流器和动力装置

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