CN110094364B - Rotor blade and axial flow compressor - Google Patents

Rotor blade and axial flow compressor Download PDF

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Publication number
CN110094364B
CN110094364B CN201810097806.5A CN201810097806A CN110094364B CN 110094364 B CN110094364 B CN 110094364B CN 201810097806 A CN201810097806 A CN 201810097806A CN 110094364 B CN110094364 B CN 110094364B
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China
Prior art keywords
rotor
groove
rotor blade
grooves
flow
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CN110094364A (en
Inventor
闫转运
南长峰
樊琳
曾瑞慧
杨俊�
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AECC Commercial Aircraft Engine Co Ltd
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AECC Commercial Aircraft Engine Co Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention aims to provide a rotor blade and an axial flow compressor. The rotor blade is suitable for being installed on a rotor drum barrel of a rotor of the axial flow compressor and comprises a blade body, a tenon and a flange plate; for two rotor blades which can be arranged on a rotor drum in a circumferential adjacent mode, a first groove structure of a suction surface part of a flange plate of one rotor blade is combined and spliced with a second groove structure of a pressure surface part of a flange plate of the other rotor blade so as to form a flow channel wall surface between the two rotor blades which are arranged in the circumferential adjacent mode, and the flow channel wall surface is provided with a plurality of grooves which are evenly distributed in a wavy mode in the circumferential direction; the groove extends along the direction from the front edge to the tail edge, and the depth of the groove is gradually increased along the extending direction; the groove extends to a termination point on the side wall surface of the platform. The existence of the groove reduces the thickness of the boundary layer, further reduces the mixing area of the interstage leakage and the boundary layer, thereby reducing the aerodynamic loss caused by the interstage leakage and improving the efficiency and surge margin of the compressor.

Description

Rotor blade and axial flow compressor
Technical Field
The invention relates to a rotor blade and an axial flow compressor.
Background
An axial compressor for a gas turbine includes a rotor and a stator. The rotor is an assembly which rotates at a high speed and applies work to the gas flow and is used for applying work to the gas entering the axial flow compressor, and the rotor comprises rotor blades. The stator is connected with the casing and comprises stator blades. In order to prevent the rotor blades rotating at high speed from rubbing against the adjacent stator blades, a gap exists between the flanges of the rotor blades and the flanges of the stator blades in the axial direction, and the gap is called an inter-stage gap. Due to the static pressure difference existing at the inlet/outlet of the stator blade row, under the action of the static pressure difference, the airflow flows from the interstage gap at the downstream of the stator blade to the upstream from the interstage gap at the upstream of the stator blade through the radial gap between the stator blade and the rotor drum and then flows into the upstream from the interstage gap at the upstream of the stator blade, and the flow is called interstage leakage. With the performance requirements of axial compressors, the stage pressure ratio becomes higher and higher, resulting in higher and higher pressure differences between the stator vane discharge inlet/outlet, which makes it difficult to completely seal the stage leakage. The interstage leakage flow tends to return to the primary flowpath in a direction nearly perpendicular to the upstream incoming flow, blending with the boundary layer of the upstream incoming flow, and causing large losses.
Therefore, there is a need in the art for a rotor blade with a better design to minimize the area where the boundary layer of the upstream incoming flow blends with interstage leakage, thereby improving compressor efficiency and surge margin.
Disclosure of Invention
The invention aims to provide a rotor blade which has the advantages of reducing the boundary layer of upstream incoming flow and the region where interstage leakage mixing occurs, and further improving the efficiency and surge margin of a compressor.
The invention also aims to provide an axial flow compressor which comprises the rotor blade, so that the axial flow compressor has the advantages of high efficiency and surge margin.
The rotor blade for realizing the purpose is suitable for being installed on a rotor drum barrel of a rotor of an axial flow compressor and comprises a blade body, a tenon and a flange plate; the blade body has a suction side and a pressure side and has a leading edge and a trailing edge in the direction of airflow; the flange plate comprises a suction surface part positioned on one side of the suction surface and a pressure surface part positioned on one side of the pressure surface; the suction surface part is provided with a first groove structure, and the pressure surface part is provided with a second groove structure;
for two of the rotor blades circumferentially adjacently arranged on the rotor drum, the first groove structure of the suction surface portion of the flange of one of the rotor blades is combined and spliced with the second groove structure of the pressure surface portion of the flange of the other one of the rotor blades to form a flow channel wall surface between the two rotor blades circumferentially adjacently arranged, wherein the flow channel wall surface is provided with a plurality of grooves which are uniformly distributed in a wave shape along the circumferential direction;
the grooves extend along the flow channel direction of the two rotor blades, and the depth of the grooves is gradually increased along the flow channel direction; the groove extends to a terminal point on the side wall surface of the flange.
The rotor blade may be further characterized in that the starting point of the groove extension is at a distance from the leading edge, and the depth of the starting point of the groove extension is zero.
The rotor blade further characterized in that the starting point of the extension of the groove is 20% to 30% of the chord length from the leading edge.
The rotor blade is further characterized in that the depth of the groove gradually changes from the starting point of the groove extension to the end point of the groove extension in a quadratic curve manner.
The rotor blade is further characterized in that the depth of the groove changes at a rate smaller in the first half than in the second half along the extension direction.
The rotor blade is further characterized in that the grooves are uniformly distributed in the circumferential direction in the form of a sine function or a cosine function.
The rotor blade is further characterized in that the positions where the grooves are respectively connected with the blade bodies of the two rotor blades are all at wave crest positions in the circumferential direction.
The rotor blade is further characterized in that, in the circumferential direction, all wave crest positions of the grooves and the original inner flow channel are located on the same molded surface, and all wave trough positions are located at the bottommost ends of the grooves.
The rotor blade may be further characterized in that the depth of the groove is less than or equal to one-half of the thickness of the platform.
The rotor blade is further characterized in that the number of the plurality of grooves is 6 to 12.
The axial-flow compressor for achieving the purpose comprises a casing, and a rotor and a stator which are arranged in the casing, and is characterized in that the rotor comprises a rotor drum barrel and the rotor blade, wherein the rotor blade is arranged on the rotor drum barrel and can rotate along with the rotor drum barrel.
The axial flow compressor is further characterized in that the stator is fixed on the casing; the stator comprises stator blades distributed in a multistage mode along the air flow direction, the stator blades extend inwards, and the rotor drum is surrounded by the labyrinth sealing structure.
The positive progress effects of the invention are as follows: the rotor blade provided by the invention is suitable for being installed on a rotor drum barrel of a rotor of an axial flow compressor and comprises a blade body, a tenon and a flange plate; the flange plate comprises a suction surface part positioned on one side of the suction surface of the blade body and a pressure surface part positioned on one side of the pressure surface of the blade body; the suction surface part is provided with a first groove structure, and the pressure surface part is provided with a second groove structure; for two rotor blades which can be arranged on a rotor drum in a circumferential adjacent mode, a first groove structure of a suction surface part of a flange plate of one rotor blade is combined and spliced with a second groove structure of a pressure surface part of a flange plate of the other rotor blade so as to form a flow channel wall surface between the two rotor blades which are arranged in the circumferential adjacent mode, and the flow channel wall surface is provided with a plurality of grooves which are evenly distributed in a wavy mode in the circumferential direction; the flow channel directions of the two rotor blades of the groove extend, and the depth of the groove gradually increases along the flow channel direction; the groove extends to a termination point on the side wall surface of the platform.
Upstream incoming flow forms a boundary layer on the flow channel wall when flowing through the flow channel wall. The thickness of the boundary layer is gradually increased along the flow passage direction. In the technical scheme of the invention, the wall surface of the flow channel is not flat, but is provided with a plurality of grooves which are uniformly distributed in a wave shape along the circumferential direction, and the depth of the grooves is gradually increased along the direction of the flow channel. Thus, the recess can better accommodate the boundary layer. Therefore, the grooves can enable the boundary layer to generate stronger vortex in the process of rotating at high speed along with the rotor drum, and further strengthen momentum exchange between the boundary layer and a main flow area of upstream incoming flow, so that the flow velocity of the upstream incoming flow close to the wall surface of a flow channel is distributed more fully along the radial direction, the thickness of the boundary layer is reduced, and further, the mixing area of interstage leakage and the boundary layer is reduced, thereby reducing the aerodynamic loss caused by the interstage leakage, and improving the efficiency and surge margin of the compressor.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a portion of an axial flow compressor of the present invention in axial cross-section showing interstage leakage;
FIG. 2 is a schematic view of two rotor blades of the present invention disposed adjacent in a circumferential direction;
FIG. 3 is a schematic view of two rotor blades of the present invention positioned adjacent to each other in the direction of airflow, showing the flow path wall;
FIG. 4 is a schematic view of two rotor blades positioned adjacent to each other against the direction of airflow in the present invention, showing the flow path wall;
FIG. 5 is a schematic illustration of a blend zone in a comparative example showing a larger blend zone;
FIG. 6 is a schematic illustration of a blending zone in the present invention showing a smaller blending zone;
FIG. 7 is a schematic illustration of a boundary layer of a comparative example showing a thicker boundary layer;
FIG. 8 is a schematic view of a facing layer of the present invention showing the facing layer being thinner.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
It should be noted that fig. 1-8 are exemplary only, are not drawn to scale, and should not be construed as limiting the scope of the invention as actually claimed.
Referring first to fig. 1, an axial compressor 100 of a gas turbine includes a rotor and a stator. The rotor is an assembly which rotates at a high speed and applies work to the gas flow and is used for applying work to the gas entering the axial flow compressor. The rotor comprises a rotor drum 1 and rotor blades 2 distributed in multiple stages in the axial direction. The rotor blade 2 comprises a blade body 20, a tenon 21 and a flange plate 22, wherein the blade body 20 and the tenon 21 are respectively fixedly arranged at the upper side and the lower side of the flange plate 22; wherein the rotor blades 2 are fixed on the rotor drum 1 by tenons 21 and can rotate along with the rotor drum 1. The rotor drum 1 is provided with corresponding mortises for cooperating with the tenons 21. The blade body 20 has a suction side 201 and a pressure side 202, and has a leading edge 20a and a trailing edge 20b in the airflow direction.
Referring to fig. 2, the flanges 22 of two adjacent rotor blades 2 of the same stage are joined together in the circumferential direction to form a flow passage wall surface C between the two adjacent rotor blades 2. Specifically, the platform 22 includes a suction surface portion 221 on the side of the suction surface 201 and a pressure surface portion 222 on the side of the pressure surface 202. After two adjacent rotor blades 2 are fixed on the rotor drum 1, the suction surface portion 221 of the rim plate 22 of one rotor blade 2 is combined and spliced with the pressure surface portion 222 of the rim plate 22 of the other rotor blade 2 to form the flow channel wall surface C. Fig. 2 also shows a joint 5 in which two flanges 22 are joined together. The upstream incoming flow F is worked by the rotor blades 2 while flowing through the flow passage wall surface C, and then flows downstream. When the upstream flow F flows through the flow path wall surface C, a boundary layer is formed on the flow path wall surface C. The principle of the boundary layer formation can be referred to the literature, and is not repeated here.
The stator is fixed on a casing 100a of the outer radius of the axial flow compressor 100 and comprises stator blades 3 distributed in a multistage manner along the airflow direction. The stator blades 3 extend inwards and surround the rotor drum 1 through the labyrinth seal 4. The stator blades 3 are disposed downstream of the rotor blades 2 of the same stage in the airflow direction. The upstream incoming flow F is rectified and diffused while flowing through the stator vanes 3.
In order to avoid rubbing between the rotor blade 2 rotating at high speed and the adjacent stator blade 3, a gap, which is called an inter-stage gap, exists between the rim plate 22 of the rotor blade 2 and the rim plate 31 of the stator blade 3 in the axial direction. Because there is a certain static pressure difference at the inlet/outlet of the stator blade row composed of the stator blades 3, under the action of the static pressure difference, an airflow F flows from the interstage gap g1 at the downstream of the stator blade 3 to the vicinity of the blade shroud 30 of the stator blade 3, through the radial gap between the blade shroud 30 of the stator blade 3 and the rotor drum 1, and then flows into the upstream flow F from the interstage gap g2 at the upstream of the stator blade 3, and the flow is also called interstage leakage.
As the performance requirements of the axial compressor 100 become higher, the stage pressure ratio becomes higher, resulting in higher and higher pressure differences between the inlet/outlet of the stator vane rows, which makes it difficult to completely seal the stage leakage. As shown in fig. 1, the inter-stage leakage flow F tends to return to the main flow channel in a direction nearly perpendicular to the upstream incoming flow F, and mixes with the flow of the upstream incoming flow F near the wall surface C of the flow channel.
As shown in fig. 7, the air flow near the flow passage wall surface C of the upstream incoming flow F includes an air flow L1 in the boundary layer and an air flow L2 near the boundary layer in the main flow region. The flow velocity S of the air flow L1 in the boundary layer is less than 99% of the flow velocity Z of the air flow L2 in the main flow region, and the flow velocity S of the air flow L1 in the boundary layer decreases closer to the flow passage wall surface C.
When the boundary layer thickness is large, the proportion of the boundary layer airflow L1 in the upstream incoming flow F near the flow channel wall surface C, which is mixed with the interstage leakage airflow F, is large, that is, when the boundary layer thickness is large, the upstream incoming flow F near the flow channel wall surface C, which is mixed with the interstage leakage airflow F, is mainly the boundary layer airflow L1, and the flow velocity of the upstream incoming flow F near the flow channel wall surface C, which is mixed with the interstage leakage airflow F, is low because the flow velocity of the boundary layer airflow L1 is low.
As shown in fig. 5, in a comparative example, the boundary layer has a large thickness, resulting in a low flow velocity V2 of the airflow near the flow path wall surface C, and a low flow velocity V1 of the airflow f of the interstage leakage. The mixing of the flow near the flow path wall surface C and the interstage leakage flow f results in a larger mixing region M1, resulting in a larger startup loss. The flow velocity V of the blended gas flow is the vector sum of the flow velocity V2 and the flow velocity V1.
To solve the above problem, it is necessary to increase the flow velocity V2 of the air flow near the flow path wall surface C. As shown in fig. 3, the suction surface part 221 has a first groove structure 221a, and the pressure surface part 222 has a second groove structure 222 a; for two rotor blades 2 which can be arranged on the rotor drum 1 in the circumferential direction adjacently, the first groove structure 221a of the suction surface part 221 of the flange plate 22 of one rotor blade 2 is combined and spliced with the second groove structure 222a of the pressure surface part 222 of the flange plate 22 of the other rotor blade 2 to form a flow channel wall surface C between the two rotor blades 2 which are arranged adjacently in the circumferential direction, and the flow channel wall surface is provided with a plurality of grooves 22a which are uniformly distributed in a wave shape in the circumferential direction;
the grooves 22a extend along the direction of the flow channels of two adjacent rotor blades 2, and the depth of the grooves 22a gradually increases along the direction of the flow channels; the groove 22a extends to a terminal point on the side wall surface of the flange 22. The side wall surface is a plane intersecting the flow path wall surface C. As shown in fig. 4, points E, F, G, H are all located on the side wall surface.
Since the depth of the groove 22a gradually increases in the extending direction, the groove 22a can better accommodate the air flow L1 in the boundary layer. Thus, the grooves 22a, during the high speed rotation of the rotor drum 1, can generate a strong vortex of the air flow L1 in the boundary layer, which enhances the momentum exchange between the air flow L1 in the boundary layer and the air flow in the main flow region, thereby reducing the thickness of the air flow L1 in the boundary layer. In comparison with fig. 7 to 8, the thickness of the air flow L2 in the main flow region close to the boundary layer increases after the thickness of the air flow L1 in the boundary layer decreases. Referring to fig. 6 again, after the technical scheme of the invention is adopted, the flow velocity V2 of the airflow close to the channel wall surface C is obviously greater than the flow velocity V2 of the airflow close to the channel wall surface C in fig. 5, so that the area of the corresponding blending region M2 is smaller, thereby reducing the aerodynamic loss caused by interstage leakage and improving the efficiency and surge margin of the compressor.
As shown in FIG. 3, in one embodiment, the groove 22a extends a distance L from the leading edge 20 a. The starting point from which the groove 22a extends is at a chord length of 20a 20% to 30% from the leading edge, and the depth at which the groove 22a extends is zero. Fig. 3 shows the starting point D from which the groove 22a extends.
In another embodiment, the depth of the groove 22a gradually changes in a quadratic curve from the beginning of the groove 22a to the end of the groove 22 a. The depth of the groove 22a varies at a rate smaller in the first half than in the second half in the extending direction.
Referring to fig. 3 and 4, the plurality of grooves 22a are uniformly distributed in the circumferential direction in the form of a sine function or a cosine function. In the circumferential direction, the positions where the plurality of grooves 22a are connected to the blade bodies 20 of the two rotor blades 2, respectively (the positions of points E, H in fig. 4) are each at a peak position.
With continued reference to fig. 4, in the circumferential direction, all the peak positions F of the plurality of grooves 22a are on the same profile as the original inner flow channels, and all the valley positions G are at the lowermost ends of the plurality of grooves 22 a.
To ensure the structural strength of platform 22, the depth of groove 22a is approximately equal to the boundary layer thickness and is less than or equal to one-half the thickness of platform 22. In one embodiment, the number of the plurality of grooves 22a is 6 to 12.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make modifications and variations without departing from the spirit and scope of the present invention.

Claims (12)

1. A rotor blade, suitable for being mounted on a rotor drum (1) of a rotor of an axial flow compressor (100), comprises a blade body (20), a tenon (21) and a flange plate (22); the blade body (20) has a suction side (201) and a pressure side (202), and has a leading edge (20a) and a trailing edge (20b) in the direction of airflow;
characterized in that the rim plate (22) comprises a suction surface portion (221) on the side of the suction surface (201) and a pressure surface portion (222) on the side of the pressure surface (202); the suction surface portion (221) having a first groove structure (221a), the pressure surface portion (222) having a second groove structure (222 a);
for two rotor blades (2) which can be arranged adjacent to each other in the circumferential direction on the rotor drum (1), the first groove structure (221a) of the suction surface portion (221) of the flange plate (22) of one of the rotor blades (2) is spliced in combination with the second groove structure (222a) of the pressure surface portion (222) of the flange plate (22) of the other rotor blade (2) to form a flow channel wall surface (C) between two rotor blades (2) which are arranged adjacent to each other in the circumferential direction, wherein the flow channel wall surface is provided with a plurality of grooves (22a) which are evenly distributed in a wave shape in the circumferential direction;
the grooves (22a) extend along the flow channel direction of the two rotor blades (2), and the depth of the grooves (22a) is gradually increased along the flow channel direction; the groove (22a) extends to a terminal point on the side wall surface of the flange (22).
2. The rotor blade according to claim 1, characterized in that the groove (22a) extends with a starting point at a distance (L) from the leading edge (20a), the depth at which the groove (22a) extends being zero.
3. The rotor blade according to claim 2, wherein the groove (22a) extends with an origin at a chord length of 20% to 30% from the leading edge (20 a).
4. The rotor blade according to claim 1, characterized in that the depth of the groove (22a) tapers in the form of a quadratic curve from the starting point of the extension of the groove (22a) to the end point of the extension of the groove (22 a).
5. The rotor blade according to claim 1, characterized in that the depth of the groove (22a) varies in the extension direction at a smaller rate in the first half than in the second half.
6. The rotor blade according to claim 1, wherein a plurality of the grooves (22a) are uniformly distributed in the circumferential direction in the form of a sine function or a cosine function.
7. The rotor blade according to claim 1, characterized in that the positions where a plurality of grooves (22a) are respectively connected to the blade bodies (20) of two rotor blades (2) in the circumferential direction are each in a peak position.
8. The rotor blade according to claim 1, wherein all peak positions of a plurality of said grooves (22a) are located on the same profile as the original inner flow channel and all valley positions are located at the lowermost ends of a plurality of said grooves (22a) in the circumferential direction.
9. The rotor blade according to claim 1, wherein the depth of the groove (22a) is less than or equal to one-half the thickness of the platform (22).
10. The rotor blade according to claim 1, wherein the number of the plurality of grooves (22a) is 6 to 12.
11. An axial flow compressor comprising a casing (100a) and a rotor and a stator arranged in the casing (100a), characterized in that the rotor comprises a rotor drum (1) and a rotor blade (2) according to any one of claims 1 to 10, the rotor blade (2) being mounted on the rotor drum (1) and being rotatable with the rotor drum (1).
12. The axial compressor according to claim 11, characterized in that said stator is fixed to said casing (100 a); the stator comprises stator blades (3) distributed in a multistage mode along the air flow direction, the stator blades (3) extend inwards, and the rotor drum barrel (1) is surrounded through a labyrinth sealing structure (4).
CN201810097806.5A 2018-01-31 2018-01-31 Rotor blade and axial flow compressor Active CN110094364B (en)

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CN111577652B (en) * 2020-05-11 2021-09-03 中国航发沈阳发动机研究所 Drum barrel structure and compressor rotor disc connecting structure thereof
CN111946666B (en) * 2020-07-20 2022-04-19 中国科学院工程热物理研究所 Axial compressor end wall boundary layer flow regulation and control structure
CN114382555A (en) * 2020-10-16 2022-04-22 中国航发商用航空发动机有限责任公司 Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate
CN113898421A (en) * 2021-10-10 2022-01-07 中国航发沈阳发动机研究所 Compressor stator inner ring and rotor stator sealing connection structure thereof
CN113914999B (en) * 2021-12-14 2022-03-18 成都中科翼能科技有限公司 Gas turbine compressor assembling method

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JPH09317696A (en) * 1996-05-27 1997-12-09 Toshiba Corp Stator blade structure of axial flow compressor
FR2989742B1 (en) * 2012-04-19 2014-05-09 Snecma UPRIGHT CAVITY COMPRESSOR HOUSING OPTIMIZED
EP3022503B1 (en) * 2013-07-15 2024-03-27 RTX Corporation Spacer for a compressor of a gas turbine.
JP6483510B2 (en) * 2015-04-14 2019-03-13 三菱日立パワーシステムズ株式会社 Gas turbine manufacturing method
CN205001254U (en) * 2015-09-29 2016-01-27 中航商用航空发动机有限责任公司 Rotor blade dish, compressor and aeroengine
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CN206449022U (en) * 2016-12-02 2017-08-29 中国航发商用航空发动机有限责任公司 Processing structure is leaked between multi stage axial flow compressor level

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