WO2019027661A1 - Diffuseur d'échappement de turbine à gaz ayant des éléments de guidage d'écoulement - Google Patents

Diffuseur d'échappement de turbine à gaz ayant des éléments de guidage d'écoulement Download PDF

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Publication number
WO2019027661A1
WO2019027661A1 PCT/US2018/042203 US2018042203W WO2019027661A1 WO 2019027661 A1 WO2019027661 A1 WO 2019027661A1 US 2018042203 W US2018042203 W US 2018042203W WO 2019027661 A1 WO2019027661 A1 WO 2019027661A1
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WO
WIPO (PCT)
Prior art keywords
flow guiding
guiding elements
gas turbine
diffuser
wall
Prior art date
Application number
PCT/US2018/042203
Other languages
English (en)
Inventor
John A. Orosa
Ulrich Waltke
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Publication of WO2019027661A1 publication Critical patent/WO2019027661A1/fr

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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • the present invention relates to gas turbines, and in particular to a gas turbine exhaust diffuser having flow guiding elements.
  • An axial flow turbomachine such as a gas turbine engine, typically includes a compressor section for compressing air, a combustor section for mixing the compressed air with fuel and igniting the mixture to form a hot working medium fluid, a turbine section for extracting power from the working medium fluid, and an exhaust diffuser located downstream of a last turbine stage for recovering static pressure of the turbine exhaust flow.
  • An exhaust diffuser may serve to reduce the losses associated to the momentum of the flow exiting the turbine section, by reducing the high velocity of the flow leaving the last stage of the turbine blading to a moderate level. The reduction in velocity decreases the kinetic energy of the flow and increases the static pressure of the flow passing through the diffuser, before the flow leaves the exhaust system or enters a heat recovery steam generator.
  • one of the bearings supporting the rotor needs to be placed in the entry region of the diffuser immediately downstream of the turbine section. This requires the placement of supporting struts crossing the diffuser flow path in a region of relatively high velocity to transmit the bearing loads to the external engine supports and ultimately to the baseplate of the engine.
  • the struts may desirably have an aerodynamic profile in order to minimize the drag of the struts and the associated loss in total pressure.
  • the direction of the flow entering the struts depends on the load set point of the engine.
  • the struts are optimized for the flow direction at base load, which is close to the axial direction, i.e. parallel to the engine center line.
  • the angle between the main flow direction and the engine center line changes towards the rotating direction of the turbine, when the engine is operated at part load conditions.
  • aspects of the present invention are directed to a gas turbine having flow guiding elements in an exhaust diffuser of the gas turbine.
  • a gas turbine comprising a turbine section, and a diffuser located downstream of a row of turbine blades of the turbine section.
  • the diffuser comprises an annular duct extending axially along a diffuser axis.
  • the annular duct is delimited radially by an outer wall and an inner wall which respectively define outer and inner boundaries of an exhaust flowpath.
  • a plurality of diffuser struts are circumferentially distributed within the annular duct. Each diffuser strut extends from the outer wall to the inner wall.
  • a plurality of flow guiding elements are circumferentially distributed within the annular duct.
  • the flow guiding elements are positioned on the inner wall and extend radially therefrom into the exhaust flowpath.
  • the flow guiding elements have an axial location downstream of the row of turbine blades and upstream of the diffuser struts.
  • the number of flow guiding elements is larger than the number of diffuser struts.
  • FIG. 1 is a schematic diagram of a gas turbine, wherein embodiments of the present invention may be employed;
  • FIG. 2 is a schematic axial end view of a diffuser section, looking in the direction of flow, according to an embodiment of the present invention
  • FIG. 3 is a radial top view of a portion of the diffuser section, looking radially inward toward a diffuser hub;
  • FIG. 4 is a meridional view of a portion of the diffuser section
  • FIG. 5 is a schematic diagram illustrating an arrangement of a flow guiding element in relation to a flow separation during operation
  • FIG. 6, 7 and 8 show radial top views of flow guiding elements having various configurations of biased leading shapes, according to a further development of the present invention.
  • a stated range is understood to include the boundary values of the range. That is, a range of X to Y is understood to include the values of X and Y.
  • a gas turbine engine 10 (or simply "gas turbine”) generally includes a compressor section 12, a combustor section 16, a turbine section 24 and an exhaust diffuser 30.
  • the compressor section 12 inducts ambient air 14 and compresses it.
  • the compressed air from the compressor section 12 enters one or more combustors in the combustor section 16.
  • the compressed air is mixed with a fuel 18, and the air-fuel mixture is burned in the combustors to form a hot gas 20, which forms a working medium fluid.
  • the hot gas 20 is routed to the turbine section 24 where it is expanded through one or more turbine stages, each turbine stage comprising a row of stationary vanes followed by a row of rotating blades.
  • the expansion of the hot gas is used to generate power that can drive a turbine rotor shaft 22.
  • the expanded gas exiting the turbine section 24 is exhausted from the engine 10 via the exhaust diffuser 30 which is located downstream of a last turbine stage.
  • the diffuser 30 is a stationary component comprising an annular duct 34 defining an exhaust flowpath and extending axially along a diffuser axis 32, which may be coaxial with the turbine rotor.
  • the annular duct 34 is delimited radially by an outer wall 36 forming an outer flowpath boundary and an inner wall 38 forming an inner flowpath boundary.
  • the outer wall 36 may be formed, for example, by a casing.
  • the inner wall 38 may be formed by a hub.
  • the annular duct 34 is typically configured to be divergent, being conical about the axis 32, which may serve to reduce the speed of the exhaust flow and thus increase the pressure difference of the exhaust gas expanding across the last stage of the turbine section 24.
  • the diffuser 30 further includes supporting structures 40, referred to as struts, which are distributed circumferentially within the annular duct 34.
  • Each strut 40 extends from the outer wall 36 to the inner wall 38, and may further extend through the outer wall 36 and the inner wall 38.
  • each strut 40 may be provided with a protective shield that forms an outer surface of the strut 40.
  • the outer surface of each strut 40 may have an aerodynamic shape, comprising a leading edge 42 and a trailing edge 44.
  • the direction of the flow entering the struts 40 depends on the load set point of the gas turbine engine.
  • the orientation of the struts 40 may be optimized for the flow direction at base load operating conditions, which is close to the axial direction, i.e. parallel to the axis 32.
  • the angle between the main flow direction and the axial direction changes towards the direction of rotation of the turbine rotor.
  • the present inventors have recognized that the high swirl or angle (in relation to the diffuser axis/ turbine rotor axis) of the flow exiting the turbine section at part load creates a radial gradient of the velocity profile with even further reduced velocity towards the inner wall of the flow path, which may result in flow separation at the inner wall immediately downstream of the last turbine stage. This flow separation may cause unsteady loads on the diffuser structure causing premature failure.
  • a diffuser 30 according to the illustrated embodiments comprises a plurality of flow guiding elements 50 circumferentially distributed within the annular duct 34.
  • the flow guiding elements 50 are positioned on the inner wall 38 and extend radially from the inner wall 38 into the exhaust flowpath.
  • the flow guiding elements 50 have an axial location which is downstream of a row of last stage turbine blades 26 and upstream of the diffuser struts 40.
  • the embodiments illustrated herein are particularly effective in reducing the swirl of the flow incident on the struts 40 near the inner wall 38 of the exhaust flowpath.
  • each flow guiding element 50 as seen in top view, extends in a length direction along a straight line from a leading edge 52 to a trailing edge 54.
  • the straight line may be parallel to the diffuser axis 32 or may be inclined thereto.
  • the angle of inclination a may lie, for example, in the range of -25 to +25 degrees, especially in the range of -10 to +10 degrees.
  • a positive (+) angle refers to an inclination in a direction U of rotation of the turbine rotor
  • a negative (-) angle refers to an inclination opposite to the direction U of rotation of the turbine rotor.
  • a positive (+) angle of inclination is illustrated.
  • the flow guiding elements 50 are axially located in a region in which flow is already separated from the inner wall 38 downstream of the last stage turbine blades 26, during operation of the gas turbine, in particular during a low power or part load operation.
  • a predicted flow separation region 70 may be determined, for example, using simulation tools, which may, for instance, be based on computational fluid dynamics (CFD) analyses.
  • the radial extension of the flow guiding elements 50 is smaller than the local distance between the outer wall 36 and the inner wall 38 of the annular duct 34.
  • the radial extension of the flow guiding elements 50 is sufficient to penetrate through the separation region 70 downstream of the last stage turbine blades 26 and to reach into the main flow.
  • the local radial height r of a flow guiding element 50 is be greater than a predicted local radial height s of the flow separation region 70 over the inner wall 38, at a specified axial location.
  • the flow guiding elements 50 are effective to turn the exhaust flow in the inner wall region towards the axial direction, thus reducing the aerodynamic load of the diffuser struts 40 and the risk of flow separation and mechanical excitation of the diffuser structure.
  • each flow guiding element 50 has a base 62 adjoining the inner wall 38 and a tip 64 opposite to the base 62.
  • the local radial height r of a flow guiding element 50 may be defined as a height of the tip 64 of the flow guiding element 50, at a specified axial location, as measured in a radial direction from the inner wall 38.
  • the local radial height r of an individual flow guiding element 50 may vary between the leading edge 52 and the trailing edge 54 of the flow guiding element 50, as shown in FIG. 4 and 5.
  • the local radial height s of the flow separation region 70 may be defined as a height of the flow separation region 70, at a specified axial location, as measured in a radial direction from the inner wall 38.
  • a high radial extension of the flow guiding elements 50 may cause aerodynamic drag and a risk of mechanical failure of the flow guiding elements 50.
  • the local radial height r of the flow guiding elements 50 may be designed to be less than or equal to 20% above the predicted local radial height s of the flow separation region 70 over the inner wall 38, at the specified axial location. Based on a different consideration, the local radial height r of the flow guiding elements 50 may be designed to lie in the range of 10 to 25%) of a local radial distance R between the outer wall 36 and the inner wall 38, at a specified axial location.
  • a local radial height at the leading edge 52 of the flow guiding element 50 is lesser than a local radial height at the trailing edge 54 of the flow guiding element 50.
  • the axial length li of the base 62 of the flow guiding element 50 is equal to or greater than the axial length 1 2 of the tip 64 of the flow guiding element 50.
  • the leading edge 52 of the flow guiding element 50 is inclined toward a downstream direction, while the trailing edge 54 of the flow guiding element 50 is inclined toward an upstream direction.
  • the axial length li of the base 62 is, in this case, greater than the axial length I2 of the tip 64.
  • the flow guiding elements 50 are desirably placed at an axial location where the flow has already separated downstream of the last stage turbine blades 26.
  • the radial height of the separation region 70 generally increases rapidly in the stream-wise or axial direction. Moving the flow guiding elements too far axially downstream may thereby increase the required radial height of the flow guiding elements 50 significantly, in order for the flow guiding elements 50 to penetrate through the flow separation region 70.
  • the present inventors recognize that an increased radial height of the flow guiding elements 50 may increase the risk of mechanical failure as well as the aerodynamic drag of the flow guiding elements 50 at base load operating conditions.
  • the present inventors further determined that moving the flow guiding elements 50 too far axially upstream may increase the risk of unfavorable excitation of the last stage turbine blades 26 by the bow waves penetrating upstream of the flow guiding elements 50.
  • the axial location of the flow guiding elements 50 may be determined to address the aforementioned conflicting requirements.
  • the flow guiding elements 50 are axially located closer to an axial position of the trailing edge 28 of the last stage turbine blades 26 than to an axial position of the leading edge 42 of the struts 40.
  • a first axial distance di may be defined between an axial position of the leading edge 52 of the flow guiding elements 50 and the axial position of the trailing edge 28 of the last stage turbine blades 26.
  • a second axial distance d 2 may be defined between the axial position of the trailing edge 28 of the last stage turbine blades 26 and the axial position of the leading edge 42 of the struts 40.
  • the axial placement of the flow guiding elements 50 may be determined such that the distance di lies in the range of 5 to 25% of the distance d 2 .
  • the axial distances di and d 2 are measured at the hub-side, i.e., at the inner wall 38.
  • the axial placement of the flow guiding elements 50 may be determined in terms of a hub side chord length of the last stage turbine blades 26, such that the distance di lies in the range of 5 to 25% of the hub side chord-length of the last stage turbine blades 26.
  • the hub side chord length of the blades 26 may be defined as a straight line distance between the leading edge and the trailing edge of the blade airfoils at the hub or inner diameter end of the blade airfoils.
  • the flow guiding elements 50 may be configured such that the ratio fP is greater than or equal to 0.75, where h is the axial length of the tip 64 of the flow guiding element 50 (see FIG. 5), and P is the pitch between circumferentially neighboring flow guiding elements 50 (see FIG. 3).
  • the flow propagating downstream of the individual flow guiding elements 50 may interact with the diffuser struts 40.
  • a further improvement may be achieved in this case by ensuring that the number of the flow guiding elements 50 is an integral multiple of the number of struts 40.
  • Such a design may allow an arrangement of the individual flow guiding elements 50 such that their circumferential position relative to the downstream struts 40 creates a pattern, which is periodically repeated along the circumference with the angular pitch of the struts 40, reducing the risk of unintended asymmetries of the flow approaching the struts 40.
  • the ratio of the number of flow guiding elements to the number of struts is seven.
  • this ratio may assume any integer value equal to or greater than two.
  • the position of the individual flow guiding elements 50 may be determined such that the wakes created by the individual flow guiding elements 50 do not impinge on the struts 40 at base load conditions.
  • the flow guiding elements 50 may be positioned with an angular offset in relation to the struts 40, such that each strut 40 has an angular position between two circumferentially neighboring flow guiding elements 50.
  • the angular offset may lie in the range of 25 to 75%, in particular about 50 %, of an angular distance between two neighboring flow guiding elements 50.
  • the flow guiding elements may be designed such that the leading edge of one or more of the flow guiding elements is aerodynamically biased toward incident flow at high power or base load operating conditions.
  • the flow guiding elements may be thereby configured to create little impact (i.e., minimum losses) at high power or base load operating conditions, while at low power or part load operating conditions, the high angle of incidence would cause vortex shedding, due to the biased shape of the leading edge.
  • Example embodiments of such flow guiding elements are illustrated in FIG. 6, 7 and 8.
  • the arrows Fi indicate the dominant direction of flow during a high power or base load operating condition
  • the arrows F 2 indicate the dominant direction of flow during a low power or part load operating condition.
  • the directions Fi and F 2 may be dependent on engine operating parameters, including but not limited to, ambient outside temperature, power output, injection of water or water vapor or implementation of other cooling devices to reduce inlet flow temperature, presence of a heat recovery steam generator (FIRSG) aft of the exhaust diffuser 30, among others.
  • the directions Fi and F 2 may be predicted for a given engine configuration, for example, based on CFD analyses.
  • the flow direction Fi at high power or base load conditions is close to parallel to the engine centerline (diffuser axis 32), or inclined slightly thereto, particularly in a direction opposite to the direction U of rotation of the turbine rotor.
  • the flow direction F 2 is inclined toward the direction U of rotation of the turbine rotor.
  • each flow guiding element 50 comprises a pressure side 56 and a suction side 58, which extend from the leading edge 52 to the trailing edge 54.
  • the pressure side 56 and suction side 58 are specified in reference to the rotation direction U, such that the pressure side 56 is positioned aft of the suction side 58 in relation to the rotation direction U.
  • the pressure side 56 and the suction side 58 may extend parallel to the length direction of the flow guiding element 50. In the illustrated embodiments of FIG.
  • the length direction of the flow guiding element 50 may be understood to be parallel to the diffuser axis 32, it being understood that the underlying concepts could be also applied to a configuration where the flow guiding elements 50 are inclined to the diffuser axis 32 (e.g. as shown in FIG. 3).
  • the leading edge 52 of the flow guiding elements 50 is aerodynamically biased toward the flow direction Fi at high power or base load operating conditions. This may be achieved by designing the flow guiding element 50 such that a first intersection 66 of the leading edge 52 with the pressure side 56 is located forward of a second intersection 68 of the leading edge 52 with the suction side 58, as seen along the length direction of the flow guiding element 50.
  • the first intersection 66 includes a sharp edge, which is configured to produce vortices 80 on the pressure side 56 of the flow guiding elements 50 at low power or part load operating conditions.
  • the formation of vortices 80 on the pressure side 56 further reduces flow separation at the inner wall of the flowpath at part load operation, thereby improving performance at part load operation with minimum losses at base load operation.
  • the leading edge 52 includes a convex curved portion 92 between the first intersection 66 and the second intersection 68.
  • the convex curved portion 92 may include, for example, a smooth elliptical shape to provide low loss at base load operation.
  • the convex curved portion 92 extends seamlessly (i.e., smoothly) from the intersection 68 and is abruptly truncated at the intersection 66 to form a sharp edge, which aids formation of vortices 80 on the pressure side 56 at part load operation.
  • the leading edge 52 includes a straight portion 96 connecting the first intersection 66 and the second intersection 68. In yet another embodiment as shown in FIG.
  • the leading edge 52 may include multiple segments 94, 96 between the first intersection 66 and the second intersection 68.
  • the segments 94, 96 may have straight or curved profiles.
  • the angle defined by the first intersection 66 is lesser than the angle defined by the second intersection 68, to produce a relatively sharp edge at the first intersection 66.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbine à gaz (10) qui comprend une section de turbine (24), et un diffuseur (30) situé en aval d'une rangée d'aubes de turbine (26) de la section de turbine (24). Le diffuseur (30) comprend un conduit annulaire (34) s'étendant axialement le long d'un axe de diffuseur (32). Le conduit annulaire (34) est délimité radialement par une paroi externe (36) et une paroi interne (38) qui définissent respectivement des limites externe et interne d'un trajet d'écoulement d'échappement. Un certain nombre d'entretoises de diffuseur (40) sont réparties de manière circonférentielle à l'intérieur du conduit annulaire (34). Chaque entretoise de diffuseur (40) s'étend depuis la paroi externe (36) jusqu'à la paroi interne (38). Une pluralité d'éléments de guidage d'écoulement (50) sont répartis de manière circonférentielle à l'intérieur du conduit annulaire (34). Les éléments de guidage d'écoulement (50) sont positionnés sur la paroi interne (38) et s'étendent radialement à partir de celle-ci dans le trajet d'écoulement d'échappement. Les éléments de guidage d'écoulement (50) ont un emplacement axial en aval de la rangée d'aubes de turbine (26) et en amont des entretoises de diffuseur (40). Le nombre d'éléments de guidage d'écoulement (50) est plus grand que le nombre d'entretoises de diffuseur (40).
PCT/US2018/042203 2017-07-31 2018-07-16 Diffuseur d'échappement de turbine à gaz ayant des éléments de guidage d'écoulement WO2019027661A1 (fr)

Applications Claiming Priority (4)

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US201762538972P 2017-07-31 2017-07-31
US62/538,972 2017-07-31
US201762549603P 2017-08-24 2017-08-24
US62/549,603 2017-08-24

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Cited By (5)

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CN112749439A (zh) * 2019-10-30 2021-05-04 沪东重机有限公司 用于拼接弯管的导流片的设置方法
CN113356947A (zh) * 2020-03-05 2021-09-07 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器支柱
CN113494317A (zh) * 2020-03-20 2021-10-12 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器的毂结构
CN113906222A (zh) * 2019-05-09 2022-01-07 诺沃皮尼奥内技术股份有限公司 用于离心式压缩机的定子叶片
CN114856717A (zh) * 2022-06-02 2022-08-05 西安交通大学 一种能增强气动性能的带分流板的新型排气扩压器结构

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EP2378072A2 (fr) * 2010-04-14 2011-10-19 Rolls-Royce Deutschland Ltd & Co KG Canal en dérivation d'un turboréacteur
EP2672080A2 (fr) * 2012-06-08 2013-12-11 General Electric Company Élément aérodynamique de moteur à turbine

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US20060269399A1 (en) * 2005-05-31 2006-11-30 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
EP2378072A2 (fr) * 2010-04-14 2011-10-19 Rolls-Royce Deutschland Ltd & Co KG Canal en dérivation d'un turboréacteur
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Publication number Priority date Publication date Assignee Title
CN113906222A (zh) * 2019-05-09 2022-01-07 诺沃皮尼奥内技术股份有限公司 用于离心式压缩机的定子叶片
CN112749439A (zh) * 2019-10-30 2021-05-04 沪东重机有限公司 用于拼接弯管的导流片的设置方法
CN113356947A (zh) * 2020-03-05 2021-09-07 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器支柱
EP3875734A1 (fr) * 2020-03-05 2021-09-08 Doosan Heavy Industries & Construction Co., Ltd. Entretoise de diffuseur d'échappement pour réduire la séparation de flux
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CN113356947B (zh) * 2020-03-05 2024-04-26 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器支柱
CN113494317A (zh) * 2020-03-20 2021-10-12 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器的毂结构
CN113494317B (zh) * 2020-03-20 2024-02-27 斗山重工业建设有限公司 减少流动剥离现象的排气扩压器的毂结构
CN114856717A (zh) * 2022-06-02 2022-08-05 西安交通大学 一种能增强气动性能的带分流板的新型排气扩压器结构
CN114856717B (zh) * 2022-06-02 2023-05-09 西安交通大学 一种能增强气动性能的带分流板的新型排气扩压器结构

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