CN113062781B - Centering and positioning structure for CMC gas turbine outer ring - Google Patents
Centering and positioning structure for CMC gas turbine outer ring Download PDFInfo
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- CN113062781B CN113062781B CN202110492152.8A CN202110492152A CN113062781B CN 113062781 B CN113062781 B CN 113062781B CN 202110492152 A CN202110492152 A CN 202110492152A CN 113062781 B CN113062781 B CN 113062781B
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- outer ring
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- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a centering and positioning structure for a CMC gas turbine outer ring, which relates to the technical field of turbine engines and comprises a CMC turbine outer ring, wherein the CMC turbine outer ring is integrally suitable for being assembled in a turbine casing; the flexible connecting structure is used for connecting the turbine casing and the CMC turbine outer ring, one end of the flexible connecting structure is fixedly connected with the turbine casing, and the other end of the flexible connecting structure is abutted against the CMC turbine outer ring; and the positioning pin integrally penetrates through the turbine casing and the flexible connecting structure, and the lower end of the positioning pin is connected with the CMC turbine outer ring. In the invention, the centering and positioning of the CMC turbine outer ring in a small space can be met by the application of the bow-shaped elastic sheet and the positioning pin; simultaneously, a plurality of impact holes through setting up carry out impingement cooling to the shell fragment, make it normally work under high temperature environment.
Description
Technical Field
The invention belongs to the technical field of turbine engines, and particularly relates to a centering and positioning structure for a CMC gas turbine outer ring.
Background
As aircraft engines place ever higher demands on performance parameters, the pre-turbine temperature is also increasing. Turbine blades, stator blades, outer rings, etc. that are in direct contact with high temperature gases are subject to significant challenges. The outer ring of the gas turbine is a special stationary part, which is not only directly eroded by the gas, but also kept centered and positioned under such a harsh environment with a suitable tip clearance from the turbine blades, which requires high temperature resistance, uniformity of thermal expansion and reliability of the connection structure.
At present, the outer ring of the gas turbine is generally made of high-temperature alloy materials, and the sectional outer ring is hung on the outer casing ring groove through a hook structure. Because the outer ring of the turbine directly contacts with high-temperature gas, the structural strength is ensured, meanwhile, the gap between the outer ring of the turbine and the turbine blade is also ensured, and the deformation caused by high temperature is prevented, so that cooling holes are arranged on the outer ring of the casing, and a large amount of cold air is introduced to cool the outer ring; there is also a design of an integral outer ring, the centering and positioning being ensured by springs.
In the prior art, the centering and positioning of the turbine outer ring depends on the ring groove of the casing, the outer ring is of a segmented structure, a gap is inevitably formed in the circumferential direction, the expansion is inevitably uneven after the outer ring is heated, and the uniformity of the blade tip gap of the turbine blade is not ensured, so that the work efficiency of the turbine is reduced. Outside the outer ring of the turbine, a large amount of cooling air needs to be introduced from the air system, which undoubtedly has a negative effect on the power of the engine. Moreover, according to the existing design experience, the temperature of the outer side of the gas turbine outer ring can reach more than 1000K, the space is limited, the volume of the designed spring is bound to be limited, the elastic modulus of the designed spring is rapidly reduced at high temperature, and the risk of rapid failure exists, so that the gas turbine outer ring generates radial displacement and the operation safety of an engine is influenced.
Accordingly, one skilled in the art provides a centering and locating structure for a CMC gas turbine outer ring to address the problems set forth in the background above.
Disclosure of Invention
An object of the present invention is to provide a centering and positioning structure for a CMC gas turbine outer ring that solves at least one aspect of the problems and drawbacks set forth in the background above.
According to one aspect of the present invention, there is provided a centering and positioning structure for a CMC gas turbine outer ring, comprising: a CMC turbine outer ring adapted to fit entirely within a turbine casing; the flexible connecting structure is used for connecting the turbine casing and the CMC turbine outer ring, one end of the flexible connecting structure is fixedly connected with the turbine casing, and the other end of the flexible connecting structure is abutted against the CMC turbine outer ring; and the positioning pin integrally penetrates through the turbine casing and the flexible connecting structure, and the lower end of the positioning pin is connected with the CMC turbine outer ring.
According to an exemplary embodiment of the invention, the CMC turbine outer ring is connected with the turbine casing through dowel pins, a plurality of bosses are uniformly arranged on the turbine casing, and a threaded through hole is arranged at the center of each boss; and the outer ring of the CMC turbine is provided with an outer ring positioning hole matched with the positioning pin, and the bottom of the positioning pin is in interference fit with the outer ring positioning hole so as to limit the axial movement of the outer ring of the CMC turbine.
According to another exemplary embodiment of the present invention, the turbine casing boss is uniformly provided with casing impact holes on both sides, and the casing impact holes can guide the external airflow of the turbine casing to cool the outside of the turbine casing.
According to another exemplary embodiment of the invention, the dowel comprises a head and a shank, the shank being integrally a threaded shank cooperating with a threaded through hole of the turbine casing; an air guide hole is formed in the positioning pin, and the air guide hole is a counter bore; the bottom of the air guide hole is provided with at least two pin impact holes which are uniformly distributed and vertical to the air guide hole.
According to another exemplary embodiment of the present invention, after the positioning pin is completely fastened, a gap is left between the bottom surface of the positioning pin and the positioning hole of the outer ring, so that the CMC outer ring can move when thermally expanded.
According to another exemplary embodiment of the invention, the pin impact holes are higher than the outer ring positioning holes in the radial direction, so that the impact airflow passing through the pin impact holes can be ensured to uniformly cover the lower surface of the arched elastic sheet, the temperature of the arched elastic sheet is reduced, and the arched elastic sheet is prevented from being influenced by high temperature to cause the reduction of the elastic modulus.
According to another exemplary embodiment of the present invention, the flexible connection structure may be made of an elastic material.
According to another exemplary embodiment of the invention, the flexible connection structure comprises a plane and two bow surfaces, the plane is fixedly connected with the turbine casing in a riveting manner, and each bow-shaped elastic sheet is riveted by 4 rivets, so that the position of the elastic sheet is ensured to be unchanged, the elastic sheet is ensured not to rotate or displace in the working process, and only radial expansion and contraction can be generated; the bow-shaped surface is abutted to the outer ring of the CMC turbine, 8 bow-shaped elastic pieces are uniformly arranged, each bow-shaped elastic piece is provided with 2 fulcrums, 16 fulcrums are abutted to the outer ring of the turbine in total, the circumferential angle between any adjacent fulcrums is equal, and compared with a traditional spring, the structure has better contact force distribution.
According to another exemplary embodiment of the invention, the casing impact hole is located above the bow surface of the flexible connection structure, so that the impact airflow passing through the casing impact hole can be ensured to uniformly cover the upper surface of the bow-shaped shrapnel, the temperature of the bow-shaped shrapnel is further reduced, and the reduction of the elastic modulus of the bow-shaped shrapnel caused by the influence of high temperature is prevented.
According to another exemplary embodiment of the invention, the CMC turbine outer ring is a monolithic structure and it employs a ceramic matrix composite with stable high temperature resistance; the ceramic matrix composite is a composite material compounded by taking ceramic as a matrix and various fibers, the ceramic matrix can be high-temperature structural ceramic such as silicon nitride, silicon carbide and the like, and the advanced ceramic has excellent performances such as high temperature resistance, high strength and rigidity, light relative weight, corrosion resistance and the like.
According to another exemplary embodiment of the invention, the composite coating with functions of abradable seal and high temperature resistance and heat insulation is sprayed on the outer ring of the CMC turbine, the composite coating can be matched with the SiC ceramic matrix composite, has good stability at high temperature, can meet the requirement of 1200 ℃ of working temperature required by a conventional turbine engine, and cannot generate phase change decomposition under a high-temperature environment, so that the outer ring of the CMC turbine fails.
According to another exemplary embodiment of the invention, one end of the outer ring of the CMC turbine is provided with a C-shaped sealing ring, and the other end of the outer ring of the CMC turbine is provided with an O-shaped sealing ring, so that the leakage of the gas in the circumferential gap of the outer ring of the CMC turbine and the leakage of the cold air of a secondary flow air system along the outer side of the outer ring of the CMC turbine are prevented.
Compared with the prior art, the invention has the beneficial effects that:
1. the turbine casing is designed and improved, and the assembly of the turbine casing, the CMC turbine outer ring, the flexible connecting structure and the positioning pin is more convenient and more stable by adding the lug boss, the threaded hole, the riveting hole and the casing impact hole.
2. The flexible connecting structure provided by the invention adopts the bow-shaped elastic sheet which can replace a traditional turbine casing and a CMC turbine outer ring centering and positioning spring; the spring in the traditional scheme has the problems that the volume of the spring is limited due to limited space, the elastic modulus of the spring is rapidly reduced at high temperature, and the spring rapidly fails to further cause radial displacement of an outer ring of a gas turbine; compared with the traditional spring, the bow-shaped elastic sheet has better high-temperature stability and contact force distribution than the spring, is more suitable for the centering and positioning of a ceramic-based turbine outer ring (CMC turbine outer ring) in a turbine casing, is not limited by space, has low requirement on the space between the CMC turbine outer ring and the casing, and can still be installed and used even in small space.
3. The arched elastic sheet is riveted with the casing, so that the position of the elastic sheet is unchanged, the elastic sheet cannot rotate or move in the working process, and only radial expansion can be generated.
4. The impact of high temperature on the elastic modulus of the elastic sheet is considered in structural design, and the pin impact holes at the bottom of the positioning pins are used for guiding impact airflow to uniformly impact and cover the lower surface of the arched elastic sheet, so that the CMC outer ring is prevented from radiating heat to the lower part of the arched elastic sheet, and the temperature of the elastic sheet is reduced.
5. The impact hole of the casing designed by the invention guides impact airflow to uniformly impact and cover the upper surface of the arched elastic sheet so as to further reduce the temperature of the elastic sheet.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a cross-sectional view of a centering and locating feature for a CMC gas turbine outer ring;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is a front view of an outer ring for a CMC gas turbine;
fig. 4 is a partially enlarged view of fig. 3.
In the figure: 1. a turbine case; 101. a threaded through hole; 102. a boss; 103. a cartridge receiver impact orifice; 2. a CMC turbine outer ring; 201. an outer ring positioning hole; 3. positioning a pin; 301. an air vent; 302. pin impact holes; 4. a flexible connection structure.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting the invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in diagram form to simplify the drawing.
According to one general technical concept of the present invention, there is provided a centering structure for a CMC gas turbine outer ring 2, comprising: a CMC outer turbine ring 2, which is integrally adapted to fit within the turbine casing 1; the flexible connecting structure 4 is used for connecting the turbine casing 1 and the CMC turbine outer ring 2, one end of the flexible connecting structure is fixedly connected with the turbine casing 1, and the other end of the flexible connecting structure is abutted against the CMC turbine outer ring 2; and the positioning pin 3 integrally penetrates through the turbine casing 1 and the flexible connecting structure 4, and the lower end of the positioning pin is connected with the CMC turbine outer ring 2.
FIG. 1 is a cross-sectional view of a centering and locating structure for a CMC gas turbine outer ring. Fig. 2 is a partially enlarged view of fig. 1. FIG. 3 is a front view of an outer ring for a CMC gas turbine. Fig. 4 is a partially enlarged view of fig. 3.
As shown in FIG. 1, in the illustrated embodiment, the CMC turbine outer ring 2 is generally adapted to fit within a turbine casing 1; a flexible connecting structure 4 is arranged between the turbine casing 1 and the CMC turbine outer ring 2, one end of the flexible connecting structure 4 is fixedly connected with the turbine casing 1, and the other end of the flexible connecting structure 4 is abutted against the CMC turbine outer ring 2 to play a role in connecting the turbine casing 1 with the CMC turbine outer ring 2; the turbine casing 1 and the flexible connecting structure 4 are integrally penetrated by the positioning pin 3, and the lower end of the positioning pin 3 is matched and connected with the CMC turbine outer ring 2.
Preferably, in actual use, the number of the flexible connecting structures 4 and the locating pins 3 is 8, and the flexible connecting structures 4 and the locating pins 3 are uniformly distributed on the whole CMC turbine outer ring 2, and bosses 102 are arranged on the outer side of the turbine casing 1 corresponding to the flexible connecting structures 4 and the locating pins 3.
As shown in fig. 4, in the illustrated embodiment, a threaded through hole 101 for cooperating with the dowel pin 3 is formed in the center of a boss 102 on the outer side of the turbine casing 1, riveting through holes are formed at four corners of the boss 102, and 4 casing impact holes 103 are uniformly formed on two sides of the boss 102 for guiding the air flow outside the turbine casing 1 to cool the outside of the turbine casing 1.
As shown in fig. 2, in the illustrated embodiment, the dowel 3 comprises a head and a shank, the whole being a threaded shank cooperating with a threaded through hole 101 of the turbine casing 1; an air guide hole 301 is formed in the positioning pin 3, and the air guide hole 301 is a counter bore; the bottom of the air guide hole 301 is provided with at least two pin impact holes 302, and the pin impact holes 302 are uniformly distributed perpendicular to the air guide hole 301.
Preferably, in actual use, as shown in fig. 2, after the locating pin 3 is completely fastened, a gap is left between the bottom surface of the locating pin and the locating hole 201 of the outer ring, so that the CMC outer ring can move when thermally expanding; the pin impact hole 302 at the bottom of the positioning pin 3 is higher than the outer ring positioning hole 201, so that the impact airflow passing through the pin impact hole 302 can be ensured to uniformly cover the lower surface of the bow-shaped elastic sheet, the temperature of the bow-shaped elastic sheet is reduced, and the bow-shaped elastic sheet is prevented from being influenced by high temperature to cause the reduction of the elastic modulus.
As shown in fig. 2, in the illustrated embodiment, the flexible connecting structure 4 may be implemented by a bow spring and all similar elastic sheet derivatives.
Preferably, in this embodiment, the flexible connection structure 4 is an arched elastic sheet, the arched elastic sheet includes a plane and two arched surfaces, the plane is fixedly connected with the turbine casing 1 in a riveting manner, and each arched elastic sheet is riveted by 4 rivets, so that the position of the elastic sheet is ensured to be unchanged, and the elastic sheet is ensured not to rotate or displace during working and only to radially stretch and retract; the bow-shaped surface is abutted to 2 outer rings of the CMC turbine, 8 bow-shaped elastic pieces are uniformly arranged, each bow-shaped elastic piece is provided with 2 fulcrums, 16 fulcrums are abutted to the outer rings of the turbine in total, the circumferential angle between any adjacent fulcrums is equal, and compared with a traditional spring, the structure has better contact force distribution.
As shown in fig. 2, in the illustrated embodiment, the casing impact hole 103 should be located above the bow surface of the bow-shaped spring, so as to ensure that the impact airflow passing through the casing impact hole 103 can uniformly cover the upper surface of the bow-shaped spring, further reducing the temperature of the bow-shaped spring, and preventing the reduction of the elastic modulus of the bow-shaped spring due to the influence of high temperature.
As shown in FIG. 1, in the illustrated embodiment, the CMC turbine outer ring 2 is a monolithic structure and employs a stable, high temperature resistant ceramic matrix composite; the ceramic matrix composite is a composite material compounded by taking ceramic as a matrix and various fibers, the ceramic matrix can be high-temperature structural ceramic such as silicon nitride, silicon carbide and the like, and the advanced ceramic has excellent performances such as high temperature resistance, high strength and rigidity, light relative weight, corrosion resistance and the like.
Preferably, in this embodiment, the CMC turbine outer ring 2 is coated with a composite coating that is abradable, tightly sealed, resistant to high temperature, and heat-insulating, the composite coating can be matched with the SiC ceramic matrix composite, and has good stability at high temperature, and can meet the 1200 ℃ working temperature requirement required by a conventional turbine engine, and it does not undergo phase change decomposition in a high temperature environment, resulting in failure of the CMC turbine outer ring 2.
Preferably, one end of the outer ring 2 of the CMC turbine is provided with a C-shaped sealing ring, and the other end of the outer ring 2 of the CMC turbine is provided with an O-shaped sealing ring, so as to prevent the gas leakage of the circumferential gap of the outer ring 2 of the CMC turbine and prevent the cold air of the secondary flow air system from leaking along the outer side of the outer ring 2 of the CMC turbine.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A centering and locating structure for a CMC gas turbine outer ring, comprising:
-a CMC turbine outer ring (2) integrally adapted to be fitted inside a turbine casing (1);
the flexible connecting structure (4) is used for connecting the turbine casing (1) and the CMC turbine outer ring (2), one end of the flexible connecting structure is fixedly connected with the turbine casing (1), and the other end of the flexible connecting structure is abutted against the CMC turbine outer ring (2);
the positioning pin (3) integrally penetrates through the turbine casing (1) and the flexible connecting structure (4), and the lower end of the positioning pin is connected with the CMC turbine outer ring (2);
the CMC turbine outer ring (2) is connected with the turbine casing (1) through a positioning pin (3), a plurality of bosses (102) are uniformly arranged on the turbine casing (1), and a threaded through hole (101) is formed in the center of each boss (102); an outer ring positioning hole (201) matched with the positioning pin (3) is formed in the CMC turbine outer ring (2);
the positioning pin (3) comprises a head part and a rod part, and the rod part is integrally a threaded rod matched with the threaded through hole (101) of the turbine casing (1); an air guide hole (301) is formed in the positioning pin (3), and the air guide hole (301) is a counter bore; the bottom of the air guide hole (301) is provided with at least two pin impact holes (302), and the pin impact holes (302) are uniformly distributed perpendicular to the air guide hole (301);
after the positioning pin (3) is completely fastened, a gap is reserved between the bottom surface of the positioning pin and the bottom of the outer ring positioning hole (201);
the pin impact hole (302) is higher than the outer ring positioning hole (201) in radial height.
2. The centering and positioning structure for the CMC gas turbine outer ring according to claim 1, wherein the turbine casing (1) boss (102) is uniformly provided with casing impact holes (103) on both sides.
3. A centring and positioning structure for CMC gas turbine outer rings according to claim 1, characterized in that the flexible connection structure (4) is made of an elastic material.
4. A structure for the centring and positioning of CMC gas turbine outer rings in accordance with claim 3, characterized in that the flexible connection structure (4) comprises a plane fixedly connected by riveting with the turbine casing (1) and two arcuate faces abutting with the CMC turbine outer ring (2).
5. A centering and positioning structure for CMC gas turbine outer ring according to claim 2, wherein the casing impact hole (103) is located above the bow face of the flexible connection structure (4).
6. A centring and positioning structure for CMC gas turbine outer ring according to any one of claims 1 to 5, characterized in that the CMC turbine outer ring (2) is of monolithic construction and it is of ceramic matrix composite material.
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| CN202110492152.8A CN113062781B (en) | 2021-05-06 | 2021-05-06 | Centering and positioning structure for CMC gas turbine outer ring |
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| CN202110492152.8A CN113062781B (en) | 2021-05-06 | 2021-05-06 | Centering and positioning structure for CMC gas turbine outer ring |
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| CN113062781B true CN113062781B (en) | 2022-07-08 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113062780B (en) * | 2021-05-06 | 2022-08-16 | 中国航发湖南动力机械研究所 | Turbine outer ring axial limit structure |
| CN114109539A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Connecting structure and method between turbine casings |
| CN114483206A (en) * | 2021-12-29 | 2022-05-13 | 西安鑫垚陶瓷复合材料有限公司 | Floating ceramic matrix composite turbine outer ring and assembling structure and method of outer ring and casing |
| US11933226B2 (en) * | 2022-05-13 | 2024-03-19 | Rtx Corporation | Heat shield and method of installing the same |
| CN115405370B (en) * | 2022-11-03 | 2023-03-10 | 中国航发沈阳发动机研究所 | Semi-elastic turbine outer ring structure |
| CN116733613B (en) * | 2023-08-10 | 2023-10-20 | 成都中科翼能科技有限公司 | Transition section structure of gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CA2806401A1 (en) * | 2012-02-22 | 2013-08-22 | General Electric Company | Low-ductility turbine shroud |
| CA2936208C (en) * | 2014-01-17 | 2018-10-30 | General Electric Company | Cmc hanger sleeve for cmc shroud |
| CN204436483U (en) * | 2015-02-04 | 2015-07-01 | 厦门大学 | A kind of turbine blade-tip gap ACTIVE CONTROL mechanism |
| US10514005B2 (en) * | 2017-02-24 | 2019-12-24 | Unison Industries, Llc | Turbine engine thermal seal |
| US10815818B2 (en) * | 2017-07-18 | 2020-10-27 | Raytheon Technologies Corporation | Variable-pitch vane assembly |
| CN207934941U (en) * | 2018-02-09 | 2018-10-02 | 天津晟泰杰电力设备技术开发有限公司 | A kind of microgap formula honeycomb seal |
| US10711630B2 (en) * | 2018-03-20 | 2020-07-14 | Honeywell International Inc. | Retention and control system for turbine shroud ring |
| CN111622810B (en) * | 2019-02-27 | 2022-05-24 | 中国航发商用航空发动机有限责任公司 | Connection device, gas turbine engine, connection piece and turbine outer ring |
| CN109751088A (en) * | 2019-03-25 | 2019-05-14 | 中国船舶重工集团公司第七0三研究所 | A kind of connecting structure of block-type turbine outer ring for marine gas turbine |
| CN112253264B (en) * | 2020-12-21 | 2021-04-02 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
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