CN114876585B - High-pressure turbine guide vane - Google Patents
High-pressure turbine guide vane Download PDFInfo
- Publication number
- CN114876585B CN114876585B CN202210641886.2A CN202210641886A CN114876585B CN 114876585 B CN114876585 B CN 114876585B CN 202210641886 A CN202210641886 A CN 202210641886A CN 114876585 B CN114876585 B CN 114876585B
- Authority
- CN
- China
- Prior art keywords
- inner ring
- support plate
- welding
- turbine
- lower edge
- 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.)
- Active
Links
- 238000003466 welding Methods 0.000 claims abstract description 112
- 238000007789 sealing Methods 0.000 abstract description 27
- 238000001816 cooling Methods 0.000 abstract description 9
- 238000009434 installation Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 6
- 239000000112 cooling gas Substances 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 5
- 239000007789 gas Substances 0.000 abstract description 3
- 238000011900 installation process Methods 0.000 abstract description 3
- 230000002411 adverse Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000011112 process operation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000005493 welding type Methods 0.000 description 1
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
- 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
-
- 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
- F01D25/12—Cooling
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of high-pressure turbine guide blades, and relates to a high-pressure turbine guide blade which comprises a blade body, an upper edge plate, a second lower edge plate and an inner ring structure; the inner side of the second lower edge plate is integrally provided with a turbine inner ring, one end of the turbine inner ring and one end of the second lower edge plate jointly form a welding surface, the other end of the turbine inner ring and the other end of the second lower edge plate jointly form a non-welding surface, and the honeycomb ring is in welding fit with the inner ring surface of the turbine inner ring; when the blade is installed, the two groups of welding areas are welded, so that the whole installation structure of the blade is compact, the installation process is simple, and the connection is firm and stable; each group of honeycomb rings and one group of second lower edge plates are combined for welding, so that the welding is more convenient; the cooling gas is ejected from the gas outlet hole at the front end of the inner ring structure, impacts the rear end region of the turbine disc, realizes simultaneous cooling of the blades and the turbine disc, and forms a comb seal structure together with the sealing disc between the turbine inner ring honeycomb and the disc in the cooling gas circulation process, thereby playing a sealing effect; the wall light wall thickness around the inner ring cavity is even, avoids intensity risks, and thoroughly solves the risk of dropping of the inner ring of the turbine in the use process.
Description
Technical Field
The application belongs to the field of high-pressure turbine guide blades, and particularly relates to a high-pressure turbine guide blade.
Background
The high-pressure turbine is positioned in the core engine of the aeroengine, and the working environment of the high-pressure turbine has the characteristics of high temperature and high pressure, and the gas temperature of the high-pressure turbine before taking off is over 1900K, so that the high-pressure turbine guide vane has higher requirements on sealing, service life and cooling.
In the design of the high-pressure turbine, besides the internal cooling structure design and the external interface structure design, the high-pressure turbine guide vane needs to be connected and matched with the inter-disk structure and has a cooling effect on the disk cavity due to the space limitation in the axial direction and the severe working environment.
At present, the connection between the guide vane and the inner ring is mainly divided into an assembly type and a welding type. The assembled connection is shown in fig. 1, the blades 1 are matched with the guide vane inner ring assembly 2, and the inner ring assembly comprises an inner ring, a honeycomb ring and other structures, and is connected by welding or bolts, so that the structure is complex and the number of parts is large. The welded connection is shown in fig. 2-3, and the blades and the inner ring are in a split design. The first guide vane 3 and the second guide vane 4 are welded in a duplex mode, the inner ring and the honeycomb are welded to form an inner ring honeycomb assembly 5, then the inner ring and the honeycomb are welded to the vane welding assembly, one end of a first lower edge plate 6 of the guide vane is combined with the end part of the inner ring of the turbine to form a fourth welding surface 7, the joint of the lower edge plate and the inner ring of the turbine is combined to form a first welding surface 8, a second welding surface 9 and a third welding surface 10, and the connectivity of the welding structure is influenced by welding manufacturability and welding quality.
The connection structure of current guide vane and inner ring exists not enough, when adopting assembled structure, has: 1) The structure is complex, and the design and the processing of a plurality of parts are involved; 2) Sufficient space is required in the axial direction; 3) The disadvantage of primary disk cooling cannot be considered.
When the assembly structure is adopted, the device comprises: 1) The thickness of the front end wall and the rear end wall of the inner ring cavity formed by the assembly has obvious difference, the structural rigidity is different, and the blade body can be adversely affected by uneven thermal deformation at two parts under a high-temperature environment; 2) The sealing between the blade assemblies is insufficient, and air leakage is possible; 3) Complex welding areas such as large-area welding, corner welding and the like exist, the manufacturability is poor, the welding flux is difficult to fill, the welding line inspection difficulty is high, the welding quality cannot be ensured, and the risk of falling off of an inner ring in the using process exists; 4) The split processing procedures are complex, and the production period is prolonged.
Therefore, how to reduce the mounting structure of the high pressure turbine guide vane, improve welding efficiency and quality is a problem to be solved.
Disclosure of Invention
The application aims to provide a high-pressure turbine guide vane which aims to solve the problems that in the prior art, an assembled structure is adopted to cause complex structure and large occupied space; and the welding structure has uneven rigidity and unstable welding quality.
The technical scheme of the application is as follows: the utility model provides a high-pressure turbine guide vane, includes the blade body, locates the upper edge plate of blade body upper end, locates the lower edge plate of blade body lower extreme, locates the inboard inner ring structure of lower edge plate, the inboard an organic whole of lower edge plate is provided with the turbine inner ring, every group turbine inner ring links to each other with a set of lower edge plate, the interior ring chamber with the inside intercommunication of blade body has been seted up between turbine inner ring and the lower edge plate, turbine inner ring and lower edge plate one end form the welding face jointly, the other end forms the non-welding face jointly, the welding face welded fit of honeycomb ring and turbine inner ring.
Preferably, the lower edge plate comprises a main support plate, a rear support plate, a front support plate and a side support plate, wherein the main support plate is connected with She Shenxiang, the rear support plate, the front support plate and the side support plate are all connected between the main support plate and the turbine inner ring, the side support plates are two groups in total and form an annular structure together with the rear support plate and the front support plate, the main support plate and the turbine inner ring are matched to form an inner ring cavity, the radial length of the front support plate is larger than that of the rear support plate, and the wall thicknesses of the rear support plate, the front support plate and the two groups of side support plates are the same.
Preferably, the welding surface is formed by encircling a main support plate, a front support plate and a turbine inner ring to form a U-shaped welding end surface, the welding surface is internally grooved, the depth of a groove on one side is not less than 3mm, the welding width of the welding surface is 0.8-1.2 times of the wall thickness of the side support plate, and the non-welding surface is a pi-shaped welding end surface.
Preferably, the non-welding surface is provided with two groups of transverse sealing grooves and two groups of radial sealing grooves, the positions of the rear support plate and the front support plate, which correspond to the non-welding surface, are respectively extended with sealing bosses, and the two groups of radial sealing grooves are respectively arranged on the two groups of sealing bosses.
Preferably, the side support plate is located on the inner side of the welding surface and the non-welding surface, and an inner concave cavity is formed by the welding surface, the non-welding surface and the side support plate in a surrounding mode.
Preferably, a shallow groove is formed in the inner side wall of the turbine inner ring, and the honeycomb ring is inserted into the shallow groove and is in welding fit with the turbine inner ring.
Preferably, the side wall of the front section of the turbine inner ring is provided with an air outlet hole communicated with the inner ring cavity.
The application relates to a high-pressure turbine guide vane, which comprises a vane body, an upper edge plate and a lower edge plate; the inner side of the lower edge plate is integrally provided with a turbine inner ring, one end of the turbine inner ring and one end of the lower edge plate form a welding surface together, the other end of the turbine inner ring and the other end of the lower edge plate form a non-welding surface together, and the honeycomb ring is matched with the inner ring surface of the turbine inner ring in a welding way; because the turbine inner ring and the lower edge plate are integrally arranged, welding is not needed between the turbine inner ring and the lower edge plate, and the welding of the two groups of welding areas is finished during installation, so that the whole installation structure of the blade is compact, the installation process is simple, and the connection is firm and stable; a group of honeycomb rings and a group of lower edge plates are combined for welding, so that the welding is more convenient; the cooling gas is ejected from the gas outlet hole at the front end of the inner ring structure, impacts the rear end region of the turbine disc, realizes simultaneous cooling of the blades and the turbine disc, and forms a comb seal structure together with the sealing disc between the turbine inner ring honeycomb and the disc in the cooling gas circulation process, thereby playing a sealing effect; the wall thickness around the inner ring cavity is even, avoids the intensity risk, has thoroughly solved the turbine inner ring risk that drops in the use simultaneously.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic view of a sectional view of a blade assembly in the prior art;
FIG. 2 is a schematic view of a welded vane explosion structure in the background art;
FIG. 3 is a schematic diagram of a blade welded side view configuration in the background;
FIG. 4 is a schematic side cross-sectional view of the present application;
FIG. 5 is a schematic view of an axial sectional structure of the present application;
FIG. 6 is a schematic diagram of an axially measured structure of the present application showing the weld face;
FIG. 7 is a schematic illustration of an axially measured structure of the present application highlighting non-welded surfaces.
1. A blade; 2. a vane inner ring assembly; 3. a first guide vane; 4. a second guide vane; 5. an inner ring honeycomb assembly; 6. a first lower edge plate; 7. a fourth welding surface; 8. a first welding surface; 9. a second welding surface; 10. a third welding surface; 11. a leaf body; 12. a turbine inner ring; 13. an inner annular cavity; 14. shallow grooves; 15. u-shaped welding end surfaces; 16. a rear support plate; 17. an air outlet hole; 18. a transverse sealing groove; 19. radial sealing grooves; 20. a front support plate; 21. a side support plate; 22. a second lower edge plate; 23. and (5) sealing the boss.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
A high pressure turbine guide vane, as shown in FIGS. 3 and 4, includes a vane body 11, an upper platform, a second lower platform 22, and an inner ring structure. The blade body 11 is arranged between the upper edge plate and the second lower edge plate 22, the inner ring structure is arranged on the inner side of the second lower edge plate 22, the inner ring structure is provided with a honeycomb ring used for sealing fit, and the honeycomb ring is matched with the comb teeth on the sealing disc between the honeycomb ring and the disc to form a sealing structure.
The turbine inner ring 12 is integrally arranged on the inner side of the second lower edge plate 22, the turbine inner ring 12 is used for positioning the honeycomb ring, the turbine inner ring 12 is connected with a group of second lower edge plates 22, an inner ring cavity 13 communicated with the inside of the blade body 11 is formed between the turbine inner ring 12 and the second lower edge plates 22, one ends of the turbine inner ring 12 and the second lower edge plates 22 jointly form a welding surface, the other ends of the turbine inner ring 12 and the second lower edge plates 22 jointly form a non-welding surface, and the honeycomb ring is in welding fit with the welding surface of the turbine inner ring 12.
The turbine inner ring 12 has two welding positions, one is that the inner ring surface of the turbine inner ring 12 is matched with the honeycomb ring in a welding way which is the same as that of the existing inner ring and honeycomb assembly; the other is a welding surface, which is used for welding and combining the left blade and the right blade in the duplex blade, the welding surface is formed by combining the second lower edge plate 22 and the turbine inner ring 12, and as the turbine inner ring 12 and the second lower edge plate 22 are integrally arranged, welding is not needed between the two, and the left blade and the right blade are welded at the welding surface to form a blade assembly during installation, and the whole installation structure of the blade 1 is compact, the installation process is simple, and the connection is firm and stable.
The cooling gas is introduced from the upper edge plate, passes through the inner cavity of the blade body 11 and then enters the inner ring cavity 13 of the second lower edge plate 22, and then can flow out through the turbine inner ring 12, and after impacting the primary turbine disk, the simultaneous cooling of the blade 1 and the turbine disk is realized.
Because the turbine inner ring 12 and the second lower edge plate 22 are integrally arranged, a welding seam structure caused by welding cannot appear in the circumferential direction of the inner ring cavity 13, stable welding fixation can be completed only through a welding surface during welding, the surrounding wall surfaces are smooth, the strength risk is avoided, and meanwhile the falling risk of the turbine inner ring 12 in the using process is thoroughly solved.
Due to the reduction of the positioning structure between the turbine inner ring 12 and the second lower edge plate 22, the related structures of the positioning groove and the positioning plate are reduced, and the weight can be effectively reduced while the positioning accuracy is ensured.
Preferably, the second lower edge plate 22 comprises a main support plate, a rear support plate 16, a front support plate 20 and a side support plate 21, wherein the main support plate is connected with the blade body 11, the rear support plate 16, the front support plate 20 and the side support plate 21 are all connected between the main support plate and the turbine inner ring 12, the side support plates 21 are in two groups, form an annular structure together with the rear support plate 16 and the front support plate 20, and form an inner ring cavity 13 together with the main support plate and the turbine inner ring 12, and the radial length of the front support plate 20 is larger than that of the rear support plate 16. The wall thickness of the rear support plate 16, the front support plate 20 and the two groups of front support plates 20 is the same, and the wall thickness range is selected from the range of 0.8-1.1 times that of the second lower edge plate 22.
By adopting the equal wall thickness treatment on the peripheral side of the inner ring cavity 13, the rigidity around the inner ring cavity 13 is the same, the thermal deformation amount in the high-temperature environment is the same, and adverse effects on the blade body 11 are avoided; however, the conventional turbine inner ring 12 needs to be designed with a positioning plate, and can be combined with the second lower edge plate 22 to form a double-layer plate structure, so that equal wall thickness cannot be realized.
With reference to fig. 5, preferably, the welding surface is surrounded by the main support plate, the front support plate 20 and the turbine inner ring 12, forming a U-shaped welding end surface 15, the welding surface is internally grooved and has a single side groove depth of not less than 3mm, and the welding width of the welding surface is 0.8-1.2 times the wall thickness of the side support plate 21. By adopting the U-shaped welding end face 15, large-area welding is avoided, complex welding areas are avoided, the problem of uneven filling of welding flux caused by large welding area is avoided to a certain extent, and meanwhile, enough welding process operation space is provided, so that welding manufacturability is improved. The non-welding surface is a pi-shaped welding end surface.
Referring to fig. 6, preferably, the non-welding surface is provided with two sets of transverse sealing grooves 18 and two sets of radial sealing grooves 19, the transverse sealing grooves 18 are formed on the main support plate, and sealing bosses 23 extend from positions of the rear support plate and the front support plate corresponding to the non-welding surface, and the two sets of radial sealing grooves are formed on the two sets of sealing bosses 23 respectively. Reliable sealing between the turbine inner ring 12, the second lower rim plate 22 and the inner ring structure is ensured by providing a transverse sealing groove 18 and a radial sealing groove 19.
Preferably, the side support plate 21 is located inside the welding surface and the non-welding surface, and an inner concave cavity is formed between the welding surface, the non-welding surface and the side support plate 21. The second lower edge plate 22 and the turbine inner ring 12 are integrally designed, so that firm and stable connection is achieved between the second lower edge plate and the turbine inner ring 12, and the weight of the whole blade 1 can be effectively reduced by arranging the inner concave cavity after sealing and structural stability are guaranteed.
Preferably, the inner side wall of the turbine inner ring 12 is provided with a shallow groove 14, the honeycomb ring is inserted into the shallow groove 14 and is in welding fit with the turbine inner ring 12, and the shallow groove 14 plays a role in welding and positioning the honeycomb blocks.
Preferably, the side wall of the front section of the turbine inner ring 12 is provided with an air outlet hole 17 communicated with the inner ring cavity 13, cooling air in the inner ring cavity 13 is led out from the air outlet hole 17 and then enters into a disc cavity of the inner ring structure to cool the primary inner ring structure, and the number and the aperture of the air outlet hole 17 are determined according to the air entraining requirement of the disc cavity.
In conclusion, the application has the advantages of more stable structure, more convenient installation, lighter weight, more convenient and efficient welding, better cooling effect and the like by adopting a simpler structure.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides a high pressure turbine guide vane, includes blade body (11), locates the upper edge board of blade body (11) upper end, locates second lower edge board (22) of blade body (11) lower extreme, locates the inboard inner ring structure of second lower edge board (22), the structural honeycomb ring that is equipped with of inner ring, its characterized in that: the inner side of the second lower edge plate (22) is integrally provided with a turbine inner ring (12), each group of turbine inner rings (12) is connected with one group of second lower edge plates (22), an inner ring cavity (13) communicated with the inside of the blade body (11) is formed between the turbine inner ring (12) and the second lower edge plate (22), one end of the turbine inner ring (12) and one end of the second lower edge plate (22) jointly form a welding surface, the other end of the turbine inner ring and the welding surface of the turbine inner ring (12) jointly form a non-welding surface, and the honeycomb ring and the welding surface of the turbine inner ring are in welding fit.
2. The high pressure turbine guide vane of claim 1 wherein: the second lower edge plate (22) comprises a main support plate, a rear support plate (16), a front support plate (20) and a side support plate (21), wherein the main support plate is connected with the blade body (11), the rear support plate (16), the front support plate (20) and the side support plate (21) are all connected between the main support plate and the turbine inner ring (12), the side support plate (21) is shared by two groups and forms an annular structure together with the rear support plate (16) and the front support plate (20), the main support plate and the turbine inner ring (12) are matched to form an inner ring cavity (13), the radial length of the front support plate (20) is larger than that of the rear support plate (16), and the wall thickness of the rear support plate (16), the front support plate (20) and the wall thickness of the two groups of the side support plates (21) are the same.
3. The high pressure turbine guide vane of claim 2 wherein: the welding surface is formed by enclosing a main support plate, a front support plate (20) and a turbine inner ring (12) to form a U-shaped welding end surface (15), the welding surface is internally grooved, the depth of a groove at one side is not less than 3mm, the welding width of the welding surface is 0.8-1.2 times the wall thickness of a side support plate (21), and the non-welding surface is a pi-shaped welding end surface.
4. The high pressure turbine guide vane of claim 2 wherein: be equipped with horizontal seal groove (18) and radial seal groove (19) on the non-welding face, horizontal seal groove (18) are total two sets of and are offered on the main tributary board, back extension board (16) and preceding extension board (20) correspond non-welding face position department and all stretch out and seal boss (23), radial seal groove (19) are total two sets of and are offered respectively on two sets of seal boss (23).
5. The high pressure turbine guide vane of any of claims 2-4 wherein: the side support plates (21) are positioned on the inner sides of the welding surface and the non-welding surface, and inner cavities are formed by the welding surface, the non-welding surface and the side support plates (21) in a surrounding mode.
6. The high pressure turbine guide vane of claim 1 wherein: shallow grooves (14) are formed in the inner side wall of the turbine inner ring (12), and the honeycomb ring is inserted into the shallow grooves (14) and is in welding fit with the turbine inner ring (12).
7. The high pressure turbine guide vane of claim 1 wherein: an air outlet hole (17) communicated with the inner ring cavity (13) is formed in the side wall of the front section of the turbine inner ring (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210641886.2A CN114876585B (en) | 2022-06-08 | 2022-06-08 | High-pressure turbine guide vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210641886.2A CN114876585B (en) | 2022-06-08 | 2022-06-08 | High-pressure turbine guide vane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114876585A CN114876585A (en) | 2022-08-09 |
| CN114876585B true CN114876585B (en) | 2024-08-02 |
Family
ID=82679540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210641886.2A Active CN114876585B (en) | 2022-06-08 | 2022-06-08 | High-pressure turbine guide vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114876585B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115142907B (en) * | 2022-09-02 | 2022-11-22 | 中国航发沈阳发动机研究所 | Integrated structure of guide vane inner ring of aero-engine |
| CN115680789A (en) * | 2022-12-29 | 2023-02-03 | 中国航发沈阳发动机研究所 | Guide vane lower edge plate mouth-biting sealing structure |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108026779A (en) * | 2015-09-14 | 2018-05-11 | 西门子股份公司 | Gas turbine is oriented to stator blade segment and manufacture method |
| CN110030037A (en) * | 2018-01-11 | 2019-07-19 | 中国航发商用航空发动机有限责任公司 | Turborotor, turborotor component and core engine |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6439837B1 (en) * | 2000-06-27 | 2002-08-27 | General Electric Company | Nozzle braze backside cooling |
| US7976274B2 (en) * | 2005-12-08 | 2011-07-12 | General Electric Company | Methods and apparatus for assembling turbine engines |
| JP5523109B2 (en) * | 2007-01-12 | 2014-06-18 | アルストム テクノロジー リミテッド | Diaphragm for turbomachine and method of manufacture |
| MY161317A (en) * | 2008-02-20 | 2017-04-14 | General Electric Technology Gmbh | Gas turbine |
| US8172504B2 (en) * | 2008-03-25 | 2012-05-08 | General Electric Company | Hybrid impingement cooled airfoil |
| US11466580B2 (en) * | 2018-05-02 | 2022-10-11 | General Electric Company | CMC nozzle with interlocking mechanical joint and fabrication |
| CN111322121A (en) * | 2020-03-06 | 2020-06-23 | 中国航发沈阳发动机研究所 | Self-sealing embedded turbine guide blade edge plate |
| CN111535869B (en) * | 2020-04-29 | 2022-07-29 | 中国航发湖南动力机械研究所 | Turbine guide |
| CN113931702B (en) * | 2020-06-29 | 2024-09-06 | 中国航发商用航空发动机有限责任公司 | Gas turbine, guide blade and guide blade edge plate thereof |
| CN113236374B (en) * | 2021-06-04 | 2023-01-17 | 中国航发沈阳发动机研究所 | Flexible connecting structure for guide blades of high-pressure turbine |
| CN216043903U (en) * | 2021-08-31 | 2022-03-15 | 浙江华燃动力科技股份有限公司 | Durable turbine guide vane |
-
2022
- 2022-06-08 CN CN202210641886.2A patent/CN114876585B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108026779A (en) * | 2015-09-14 | 2018-05-11 | 西门子股份公司 | Gas turbine is oriented to stator blade segment and manufacture method |
| CN110030037A (en) * | 2018-01-11 | 2019-07-19 | 中国航发商用航空发动机有限责任公司 | Turborotor, turborotor component and core engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114876585A (en) | 2022-08-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114876585B (en) | High-pressure turbine guide vane | |
| CN103184894B (en) | Platform chiller and its manufacture method for turbine rotor blade | |
| JP4513000B2 (en) | Method and apparatus for assembling a gas turbine engine | |
| JP6030826B2 (en) | Apparatus and method for cooling the platform area of a turbine rotor blade | |
| US8814518B2 (en) | Apparatus and methods for cooling platform regions of turbine rotor blades | |
| JP6344869B2 (en) | Turbine vane, turbine, and method for modifying turbine vane | |
| CA2715596C (en) | Fabricated static vane ring | |
| JP5898898B2 (en) | Apparatus and method for cooling the platform area of a turbine rotor blade | |
| US9810097B2 (en) | Corrugated mid-turbine frame thermal radiation shield | |
| JP2004257389A (en) | Cantilever support for turbine nozzle segment | |
| JPS61145303A (en) | Improved coolable stator assembly of rotary machine | |
| JP2012102726A (en) | Apparatus, system and method for cooling platform region of turbine rotor blade | |
| US20170114648A1 (en) | Turbine bucket having cooling passageway | |
| US8814517B2 (en) | Apparatus and methods for cooling platform regions of turbine rotor blades | |
| CN104033186B (en) | Gas turbine blades | |
| JP2000104502A (en) | Simultaneous machining junction aerofoil | |
| CN110159359A (en) | A kind of partition and its processing method of steam turbine | |
| CN103423774A (en) | Sealed connecting structure of combustion chamber flame tube with pressure stabilizing chamber and transition section | |
| CN203464335U (en) | Sealed connecting structure of combustion chamber flame tube with pressure stabilizing cavity and transition section | |
| KR20160034888A (en) | Gas turbine high-temperature component, gas turbine with same and method for producing gas turbine high-temperature component | |
| JP5632812B2 (en) | Gas turbine blade | |
| CN114585802B (en) | Turbine blade, method of manufacturing a turbine blade and method of refurbishing a turbine blade | |
| EP3043031B1 (en) | Vane assembly, vane set, and method of manufacturing a vane assembly | |
| JP7232035B2 (en) | Gas turbine stator blades and gas turbines | |
| CN102943711A (en) | Device for cooling guiding device group of turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221104 Address after: 1901 MoMA building, 199 Chaoyang North Road, Chaoyang District, Beijing 100020 Applicant after: BEIJING QINGRUAN CHUANGXIANG INFORMATION TECHNOLOGY Co.,Ltd. Applicant after: AECC SHENYANG ENGINE Research Institute Address before: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Applicant before: AECC SHENYANG ENGINE Research Institute |
|
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221125 Address after: 1901 MoMA building, 199 Chaoyang North Road, Chaoyang District, Beijing 100020 Applicant after: BEIJING QINGRUAN CHUANGXIANG INFORMATION TECHNOLOGY Co.,Ltd. Applicant after: AECC SHENYANG ENGINE Research Institute Address before: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Applicant before: AECC SHENYANG ENGINE Research Institute |
|
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221228 Address after: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Applicant after: AECC SHENYANG ENGINE Research Institute Address before: 1901 MoMA building, 199 Chaoyang North Road, Chaoyang District, Beijing 100020 Applicant before: BEIJING QINGRUAN CHUANGXIANG INFORMATION TECHNOLOGY Co.,Ltd. Applicant before: AECC SHENYANG ENGINE Research Institute |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |