CN114876585A - High-pressure turbine guide vane - Google Patents
High-pressure turbine guide vane Download PDFInfo
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- CN114876585A CN114876585A CN202210641886.2A CN202210641886A CN114876585A CN 114876585 A CN114876585 A CN 114876585A CN 202210641886 A CN202210641886 A CN 202210641886A CN 114876585 A CN114876585 A CN 114876585A
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- inner ring
- support plate
- turbine
- welding
- blade
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- 238000003466 welding Methods 0.000 claims abstract description 96
- 238000007789 sealing Methods 0.000 claims abstract description 36
- 238000009434 installation Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 5
- 239000000112 cooling gas Substances 0.000 abstract description 4
- 238000011900 installation process Methods 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 description 6
- 238000005493 welding type Methods 0.000 description 3
- 230000002411 adverse Effects 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
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000007789 gas Substances 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
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Classifications
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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
- 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
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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
- F01D25/12—Cooling
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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
- 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
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- 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; an inner turbine ring is integrally arranged on the inner side of the second lower edge plate, the inner turbine ring and one end of the second lower edge plate jointly form a welding surface, the other end of the second lower edge plate jointly forms a non-welding surface, and the honeycomb ring is in welding fit with the inner ring surface of the inner turbine ring; when the blade is installed, the two groups of welding areas are welded, and 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 is combined with one group of second lower edge plates for welding, so that the welding is more convenient; cooling gas is ejected from the air outlet hole at the front end of the inner ring structure to impact the rear end region of the turbine disc, so that the blades and the turbine disc are cooled simultaneously, and a labyrinth sealing structure is formed by the turbine inner ring honeycomb and the sealing disc between the inner ring honeycomb and the disc in the circulation process of the cooling gas, so that a sealing effect is achieved; the smooth wall thickness of the wall surface around the inner ring cavity is uniform, the intensity risk is avoided, and the risk that the inner ring of the turbine falls in the use process is thoroughly solved.
Description
Technical Field
The application belongs to the high-pressure turbine guide vane field, in particular to a high-pressure turbine guide vane.
Background
The high-pressure turbine is positioned in a core machine of the aircraft engine, 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 reaches over 1900K before takeoff, so that the guide blade of the high-pressure turbine has higher requirements in the aspects of sealing, service life and cooling.
In the design of a high-pressure turbine, the high-pressure turbine guide vane needs to be subjected to internal cooling structural design and external interface structural design, and needs to be connected and matched with a disc-to-disc structure and cool a disc cavity due to the fact that the high-pressure turbine guide vane is limited in space in the axial direction and the working environment is severe.
At present, the connection between the guide blade and the inner ring is mainly divided into an assembling type and a welding type. The assembled connection is as shown in figure 1, the blade 1 is matched with the guide vane inner ring component 2, the inner ring component comprises an inner ring, a honeycomb ring and other structures, and the inner ring component is connected by welding or bolts, so that a plurality of parts and a complex structure are provided. The welded connection is as shown in fig. 2-3, with the blades and inner ring in split design. The first guide blade 3 and the second guide blade 4 are welded in a duplex mode, the turbine inner ring 12 and the honeycomb ring 24 are welded into an inner ring honeycomb assembly 5 and then welded with the blade welding assembly, one end of the first lower edge plate 6 of the guide blade and the end portion of the turbine inner ring are combined to form a fourth welding surface 7, the connection portion of the lower edge plate and the turbine inner ring is combined to form a first welding surface 8, a second welding surface 9 and a third welding surface 10, and the welding structure connectivity is affected by welding manufacturability and welding seam quality.
The connection structure of current guide blade and inner ring exists not enoughly, when adopting the 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 taken into account.
When the assembly structure is adopted, the structure has the following advantages: 1) the thicknesses of the front end wall and the rear end wall of an inner ring cavity formed by the assembly are obviously different, the structural rigidity is different, and the blade body can be adversely affected by the uneven thermal deformation of two positions in a high-temperature environment; 2) the sealing between the blade assemblies is insufficient, and the possibility of air leakage exists; 3) the method has the advantages that 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 seam inspection difficulty is high, the welding quality cannot be guaranteed, and the risk of falling of the inner ring in the use process exists; 4) complicated split processing procedures and prolonged production period.
Therefore, how to reduce the installation structure of the guide vane of the high-pressure turbine and improve the welding efficiency and quality is a problem to be solved.
Disclosure of Invention
The application aims to provide a high-pressure turbine guide vane to solve the problems that the structure is complex and the occupied space is large due to the adoption of an assembly structure in the prior art; the problems of uneven rigidity and unstable welding quality of the welding structure are solved.
The technical scheme of the application is as follows: the utility model provides a high-pressure turbine guide vane, includes the blade, locate the upper flange plate of blade upper end, locate the lower flange plate of blade lower extreme, locate the inboard inner ring structure of lower flange plate, the structural honeycomb ring that is equipped with of inner ring, the inboard an organic whole of lower flange plate is provided with the turbine inner ring, every group the turbine inner ring links to each other with a set of lower flange plate, set up the inner ring chamber with the inside intercommunication of blade between turbine inner ring and the lower flange plate, the turbine inner ring forms the non-weld face with lower flange plate one end jointly, the other end forms the non-weld face jointly, the inner ring welding cooperation 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 side support plates, the main support plate is connected with the blade body, the rear support plate, the front support plate and the side support plates are connected between the main support plate and the inner ring of the turbine, the side support plates are divided into two groups, the two groups of side support plates, the rear support plate and the front support plate form an annular structure, an inner ring cavity is formed by matching the main support plate and the inner ring of the turbine, the radial length of the front support plate is greater 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 surrounding a main support plate, a front support plate and a turbine inner ring to form a U-shaped welding end face, the welding surface is provided with a groove inwards, the depth of the 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 forms a Pi-shaped welding end face.
Preferably, the non-welding surface is provided with two groups of transverse sealing grooves and two groups of radial sealing grooves, the two groups of transverse sealing grooves are formed in the main support plate, sealing bosses extend out of positions, corresponding to the non-welding surface, of the rear support plate and the front support plate, and the two groups of radial sealing grooves are formed in the two groups of sealing bosses respectively.
Preferably, the side support plate is located at the inner side of the welding surface and the non-welding surface, and an inner concave cavity is defined between the welding surface and the side support plate and between the non-welding surface and the side support plate.
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 inner ring of the turbine is provided with an air outlet hole communicated with the inner ring cavity.
The application discloses 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, the turbine inner ring and one end of the lower edge plate jointly form a welding surface, the other end of the turbine inner ring and one end of the 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; 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, two groups of welding areas are welded during installation, and 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; cooling gas is ejected from the air outlet hole at the front end of the inner ring structure to impact the rear end region of the turbine disc, so that the blades and the turbine disc are cooled simultaneously, and a labyrinth sealing structure is formed by the turbine inner ring honeycomb and the sealing disc between the inner ring honeycomb and the disc in the circulation process of the cooling gas, so that a sealing effect is achieved; the wall thickness is even around the inner ring chamber, avoids the intensity risk, has thoroughly solved simultaneously in the use the risk that the turbine inner ring drops.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a sectional view of a blade assembly of the prior art;
FIG. 2 is a schematic diagram of a blade welding type explosive structure in the prior art;
FIG. 3 is a schematic side view of a blade welding type in the prior art;
FIG. 4 is a side cross-sectional structural schematic view of the present application;
FIG. 5 is a schematic cross-sectional axial view of the present application;
FIG. 6 is a schematic view of an axial structure of a highlighted weld face of the present application;
FIG. 7 is a schematic axial view of the present application highlighting the non-welded surface.
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 weld face; 8. a first welding surface; 9. a second weld face; 10. a third weld face; 11. a leaf body; 12. a turbine inner ring; 13. an inner ring cavity; 14. shallow-groove; 15. a U-shaped welding end face; 16. a rear support plate; 17. an air outlet; 18. a transverse sealing groove; 19. a radial sealing groove; 20. a front support plate; 21. a side support plate; 22. a second lower flange; 23. sealing the boss; 24. a honeycomb ring; 25. a main support plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A high-pressure turbine guide vane, as shown in FIGS. 3 and 4, comprises a blade body 11, an upper edge plate, a second lower edge plate 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 24 used for sealing and matching, and the honeycomb ring 24 and the labyrinth teeth on the sealing disc between discs are matched to form a sealing structure.
The inboard integrative turbine inner ring 12 that is provided with of second lower flange 22, turbine inner ring 12 is used for playing the effect of location to honeycomb ring 24, turbine inner ring 12 links to each other with a set of second lower flange 22, set up the inner ring chamber 13 with the inside intercommunication of blade 11 between turbine inner ring 12 and the second lower flange 22, turbine inner ring 12 forms the face of weld jointly with second lower flange 22 one end, the other end forms non-face of weld jointly, honeycomb ring 2424 adopts current welding cooperation structure honeycomb ring 24 with the cooperation of 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 welded and matched with the honeycomb ring 24, and the welding mode of the position is the same as that of the existing inner ring and honeycomb component; the other is a welding surface, which is used for welding and combining the left blade and the right blade in the double-linked blade, the welding surface is formed by combining the second lower edge plate 22 and the turbine inner ring 12, the turbine inner ring 12 and the second lower edge plate 22 are integrally arranged, welding is not needed between the two, the left blade and the right blade are welded at the welding surface to form a blade assembly when the blades are installed, 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 air is introduced from the upper edge plate, enters the inner ring cavity 13 of the second lower edge plate 22 after passing through the inner cavity of the blade body 11, and then can flow out through the inner ring 12 of the turbine to impact the first-stage turbine disc, so that the blades 1 and the turbine disc are cooled simultaneously.
Because turbine inner ring 12 sets up with the second is integrative down the flange 22, then inner ring chamber 13 circumference can not appear by the welding seam structure that the welding leads to, only need can accomplish stable welded fastening through the face of weld when the welding, and the wall is smooth around it, avoids the intensity risk, has thoroughly solved the risk that drops of turbine inner ring 12 in the use simultaneously.
Because the positioning structure between the turbine inner ring 12 and the second lower edge plate 22 is reduced, the related structures of the positioning grooves and the positioning plates are reduced, and the weight can be effectively reduced while the positioning precision is ensured.
Preferably, the second lower edge plate 22 comprises a main support plate 25, a rear support plate 16, a front support plate 20 and side support plates 21, the main support plate 25 is connected with the blade body 11, the rear support plate 16, the front support plate 20 and the side support plates 21 are connected between the main support plate 25 and the turbine inner ring 12, the side support plates 21 form two groups in total and form an annular structure together with the rear support plate 16 and the front support plate 20, an inner ring cavity 13 is formed by matching the main support plate 25 and the turbine inner ring 12, and the radial length of the front support plate 20 is greater than that of the rear support plate 16. The wall thicknesses of the rear support plate 16, the front support plate 20 and the two groups of front support plates 20 are the same, and the wall thickness range is selected from the range of 0.8-1.1 times of the wall thickness of the second lower edge plate 22.
By adopting 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 under a high-temperature environment is also the same, and adverse effects on the blade body 11 are avoided; 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 achieved.
With reference to fig. 5, preferably, the welding surface is enclosed by the main support plate 25, the front support plate 20 and the turbine inner ring 12 to form a U-shaped welding end surface 15, the welding surface is grooved inwards, the depth of the groove on one side is 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, a complex welding area cannot occur, the problem of uneven filling of welding flux caused by large welding area is avoided to a certain extent, meanwhile, enough welding process operation space is provided, and welding manufacturability is improved. The non-welding surface forms 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 two sets of transverse sealing grooves 18 are formed in the main support plate 25, the positions of the rear support plate and the front support plate corresponding to the non-welding surface extend out of the sealing bosses 23, and the two sets of radial sealing grooves are formed in the two sets of sealing bosses 23 respectively. Reliable sealing between the turbine inner ring 12, the second lower flange 22 and the inner ring structure is ensured by the arrangement of the transverse sealing grooves 18 and the radial sealing grooves 19.
Preferably, the side support plate 21 is located at the inner side of the welding surface and the non-welding surface, and an inner concave cavity is defined between the welding surface and the non-welding surface and the side support plate 21. Due to the integral design of the second lower edge plate 22 and the turbine inner ring 12, the connection between the second lower edge plate and the turbine inner ring is firm and stable, and the weight of the whole blade 1 can be effectively reduced by arranging the inner concave cavity after the sealing and the 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 24 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 block.
Preferably, the side wall of the front section of the inner ring 12 of the turbine is provided with an air outlet 17 communicated with the inner ring cavity 13, cooling air in the inner ring cavity 13 enters the disc cavity of the inner ring structure after being led out from the air outlet 17 to cool the one-stage inner ring structure, and the number and the aperture of the air outlet 17 are determined according to the air-entraining requirement of the disc cavity.
To sum up, this application has realized through adopting more simple structure that the structure is more stable, the installation is more convenient, weight is lighter, the welding is more convenient multiple advantages such as high efficiency, cooling effect are better.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of 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 (11), locates the upper flange of blade (11) upper end, locates second lower flange (22) of blade (11) lower extreme, locates the inboard inner ring structure of second lower flange (22), be equipped with honeycomb ring (24) on the inner ring structure, its characterized in that: second bottom edge board (22) inboard an organic whole is provided with turbine inner ring (12), every group turbine inner ring (12) link to each other with a set of second bottom edge board (22), set up between turbine inner ring (12) and second bottom edge board (22) inner ring chamber (13) with the inside intercommunication of blade (11), turbine inner ring (12) and second bottom edge board (22) one end form the face of weld, the other end forms non-face of weld honeycomb ring (24) jointly.
2. The high pressure turbine guide vane of claim 1, wherein: the second lower edge plate (22) comprises a main support plate (25), a rear support plate (16), a front support plate (20) and side support plates (21), the main support plate (25) is connected with the blade body (11), the rear support plate (16), the front support plate (20) and the side support plates (21) are connected between the main support plate (25) and the turbine inner ring (12), the side support plates (21) are divided into two groups and form an annular structure with the rear support plate (16) and the front support plate (20), the main support plate (25) 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 thicknesses of the rear support plate (16), the front support plate (20) and the two groups of side support plates (21) are the same.
3. The high pressure turbine guide vane of claim 2, wherein: the welding surface is formed by surrounding a main support plate (25), a front support plate (20) and a turbine inner ring (12) to form a U-shaped welding end surface (15), the welding surface is inwards grooved, the depth of a single-side groove is not less than 3mm, the welding width of the welding surface is 0.8-1.2 times of the wall thickness of a side support plate (21), and a non-welding surface forms a Pi-shaped welding end surface.
4. The high pressure turbine guide vane of claim 2, wherein: the non-welding surface is provided with transverse sealing grooves (18) and radial sealing grooves (19), the transverse sealing grooves (18) are divided into two groups and are arranged on a main support plate (25), sealing bosses (23) extend out of positions, corresponding to the non-welding surface, of a rear support plate (16) and a front support plate (20), and the radial sealing grooves (19) are divided into two groups and are arranged on the two groups of sealing bosses (23) respectively.
5. The high pressure turbine guide vane as claimed in any one of claims 2 to 4, wherein: the side support plate (21) is located on the inner side of the welding surface and the non-welding surface, and an inner concave cavity is defined by the welding surface, the non-welding surface and the side support plate (21).
6. The high pressure turbine guide vane of claim 1, wherein: the inner side wall of the turbine inner ring (12) is provided with a shallow groove (14), and the honeycomb ring (24) is inserted into the shallow groove (14) and is in welding fit with the turbine inner ring (12).
7. The high pressure turbine guide vane of claim 1, wherein: and 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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210641886.2A CN114876585A (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 CN114876585A (en) | 2022-06-08 | 2022-06-08 | High-pressure turbine guide vane |
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| Publication Number | Publication Date |
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| CN114876585A true CN114876585A (en) | 2022-08-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210641886.2A Pending CN114876585A (en) | 2022-06-08 | 2022-06-08 | High-pressure turbine guide vane |
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| CN (1) | CN114876585A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115142907A (en) * | 2022-09-02 | 2022-10-04 | 中国航发沈阳发动机研究所 | Aeroengine stator inner ring integrated structure |
| 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 |
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| CN113236374A (en) * | 2021-06-04 | 2021-08-10 | 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 |
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| 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 |
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