CN111535869B

CN111535869B - Turbine guide

Info

Publication number: CN111535869B
Application number: CN202010355186.8A
Authority: CN
Inventors: 于晶; 叶炜; 吕学敏; 屈彬
Original assignee: Hunan Aviation Powerplant Research Institute AECC
Current assignee: Hunan Aviation Powerplant Research Institute AECC
Priority date: 2020-04-29
Filing date: 2020-04-29
Publication date: 2022-07-29
Anticipated expiration: 2040-04-29
Also published as: CN111535869A

Abstract

The utility model relates to the technical field of aeroengines, and provides a turbine guider, which comprises a turbine casing and a guide vane of a perforated plate ring, wherein the perforated plate ring is connected to the outer side of the turbine casing; the guide blades are connected to the inner side of the turbine casing; wherein the turbine case, the orifice ring, and the guide vanes are of a one-piece construction. The turbine guider of this disclosure sets up turbine casing, orifice plate ring and guide vane into the monolithic structure, can effectively reduce the part quantity of turbine guider, simple structure, and the reliability is high to the comparatively complicated problem of turbine guider structure among the prior art has been solved.

Description

Turbine guide

Technical Field

The disclosure relates to the technical field of aircraft engines, in particular to a turbine guider.

Background

In the existing gas turbine engine and ground gas turbine, a gas turbine guider is one of important stator parts and runner parts, is positioned at the foremost end of a turbine part and mainly used for changing the direction of airflow, expanding and accelerating gas and converting potential energy of high-temperature gas into kinetic energy. The turbine casing and the turbine outer ring mainly play a role in supporting, containing and controlling blade tip clearance.

The existing gas turbine guider is generally formed by combining guide vane sector parts, and the sector parts are fixed through a guider bracket; the turbine outer ring is usually designed in a segmented manner, and is designed into a fan-shaped segment with a hook, and the fan-shaped segment is connected with the turbine casing through the hook. Because the gas turbine guider and the turbine outer ring are formed by combining the fan-shaped parts, the guider mounting bracket causes more parts, more matched precise structure sizes, complex mounting, high processing cost and poor reliability, and the more parts can cause the weight of the engine to be increased.

Disclosure of Invention

The present disclosure provides a turbine guide to solve the problem that the structure of a turbine guide in the prior art is complex.

The present invention provides a turbine nozzle comprising:

a turbine case;

an orifice ring connected to an outer side of the turbine case;

a guide vane connected to an inner side of the turbine case;

wherein the turbine case, the orifice ring, and the guide vanes are of a one-piece construction.

In one embodiment of the invention, the orifice ring is welded to the turbine case.

In one embodiment of the invention, the guide vanes are welded to the turbine casing.

In one embodiment of the invention, the guide vanes are cast vanes.

In one embodiment of the invention, the guide vane comprises a plurality of vane segments, which are arranged in sequence in the circumferential direction of the turbine casing;

wherein the plurality of blade segments are all independently shaped.

In one embodiment of the present invention, the blade segment includes a welded end and a free end, the welded end is welded to the turbine casing, a gap is reserved between two adjacent free ends, and the turbine nozzle further includes:

and the sealing sheet is arranged between the two adjacent free ends so as to seal the reserved gap.

In one embodiment of the invention, a plurality of welding grooves are arranged on the turbine casing, and the plurality of welding grooves are arranged corresponding to the plurality of blade sections one by one;

the welding ends of the blade sections are arranged in the welding grooves, and the welding ends are matched with the welding grooves.

In one embodiment of the invention, a cooling flow passage is provided between the orifice ring and the turbine casing, and the orifice ring is provided with a through hole communicating with the cooling flow passage.

In one embodiment of the invention, the guide vanes have an inner cavity in communication with the cooling flow passage, the inner cavity being in communication with the inside of the turbine case.

In one embodiment of the invention, the inner surface of the turbine casing is provided with a thermal barrier coating.

According to the turbine guide device, the turbine casing, the orifice plate ring and the guide blades are arranged into an integral structure, so that the number of parts of the turbine guide device can be effectively reduced, the structure is simple, the reliability is high, and the problem that the structure of the turbine guide device in the prior art is complex is solved.

Drawings

Various objects, features and advantages of the present disclosure will become more apparent from the following detailed description of preferred embodiments thereof, when considered in conjunction with the accompanying drawings. The drawings are merely exemplary illustrations of the disclosure and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:

FIG. 1 is a cross-sectional structural schematic view of a turbine nozzle shown in accordance with an exemplary embodiment;

FIG. 2 is a partial structural schematic view of a turbine nozzle according to an exemplary embodiment.

The reference numerals are explained below:

10. a turbine case; 11. a cooling flow channel; 12. welding a groove; 20. an orifice ring; 21. a through hole; 30. a guide blade; 31. a blade segment; 311. welding the end; 312. a free end; 32. reserving a gap; 40. a sealing sheet; 50. a thermal barrier coating; 60. a first stage working blade; 70. and a secondary working blade.

Detailed Description

Exemplary embodiments that embody features and advantages of the present disclosure are described in detail below in the specification. It is to be understood that the disclosure is capable of various modifications in various embodiments without departing from the scope of the disclosure, and that the description and drawings are to be regarded as illustrative in nature, and not as restrictive.

In the following description of various exemplary embodiments of the disclosure, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the disclosure may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present disclosure. Moreover, although the terms "over," "between," "within," and the like may be used in this specification to describe various example features and elements of the disclosure, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples in the figures. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of this disclosure.

An embodiment of the present invention provides a turbine nozzle, referring to fig. 1 and 2, the turbine nozzle comprising: a turbine case 10; an orifice ring 20, the orifice ring 20 being attached to the outside of the turbine case 10; a guide vane 30, the guide vane 30 being connected to an inner side of the turbine casing 10; wherein the turbine case 10, the orifice ring 20, and the guide vanes 30 are of a one-piece construction.

According to the turbine guide device provided by the embodiment of the invention, the turbine casing 10, the orifice plate ring 20 and the guide blades 30 are arranged into an integral structure, so that the number of parts of the turbine guide device can be effectively reduced, the structure is simple, the reliability is high, and the problem that the structure of the turbine guide device in the prior art is complex is solved.

In one embodiment, the orifice ring 20 is welded to the turbine case 10. The orifice plate ring 20 and the turbine casing 10 can be formed independently and then welded into an integral structure, which not only ensures convenient processing, but also ensures that the connection between the orifice plate ring 20 and the turbine casing 10 does not need to increase other parts, thereby reducing the number of parts of the turbine guider, and the welding can improve the connection stability of the orifice plate ring 20 and the turbine casing 10.

In one embodiment, the guide vanes 30 are welded to the turbine case 10. The guide vane 30 and the turbine casing 10 can be formed independently and then welded into an integral structure, which not only ensures convenient processing, but also ensures that the connection between the guide vane 30 and the turbine casing 10 does not need to increase other parts, thereby reducing the number of parts of the turbine guide, and the welding can improve the connection stability of the guide vane 30 and the turbine casing 10.

In one embodiment, the guide vanes 30 are cast vanes, thereby improving the manufacturing efficiency and structural stability of the guide vanes 30.

In one embodiment, as illustrated in fig. 1 and 2, the guide vane 30 includes a plurality of vane segments 31, the plurality of vane segments 31 being sequentially arranged in a circumferential direction of the turbine casing 10; wherein the plurality of blade segments 31 are each independently formed. The guide vane 30 is formed by combining a plurality of vane segments 31, and after each vane segment 31 is independently formed, the vane segments are sequentially welded to the turbine casing 10, and since each vane segment 31 can be independently welded, the overall welding difficulty is reduced.

In one embodiment, as shown in fig. 1 and 2, the blade segment 31 includes a welding end 311 and free ends 312, the welding end 311 is welded to the turbine casing 10, two adjacent free ends 312 have a reserved gap 32 therebetween, and the turbine guider further includes: and a sealing sheet 40, wherein the sealing sheet 40 is arranged between two adjacent free ends 312 to close the reserved gap 32. Considering that the blade segment 31 may deform during use, the reserved gap 32 is formed between two adjacent free ends 312, and the reserved gap 32 may cause gas leakage, so that the sealing sheet 40 performs sealing, and gas leakage may be effectively prevented on the basis of ensuring the existence of the reserved gap 32.

In one embodiment, as shown in fig. 1 and 2, a plurality of welding slots 12 are provided on the turbine casing 10, the plurality of welding slots 12 being provided in one-to-one correspondence with the plurality of blade segments 31; wherein the welding end 311 of the blade segment 31 is arranged in the welding groove 12, and the welding end 311 is adapted to the welding groove 12. The weld groove 12 is a lobed groove, i.e. matching the profile of the weld end 311 of the blade segment 31, and is fixed to the turbine casing 10 by welding after the weld end 311 is inserted into the weld groove 12.

In one embodiment, as shown in FIG. 1, a cooling channel 11 is provided between the orifice ring 20 and the turbine casing 10, and the orifice ring 20 is provided with a through hole 21 communicating with the cooling channel 11. The cooling flow passage 11 is a small gap flow passage, and cool air enters the cooling flow passage 11 through the through hole 21, thereby cooling the turbine casing 10.

In one embodiment, the guide vanes 30 have an inner cavity in communication with the cooling flow passage 11, the inner cavity being in communication with the inside of the turbine casing 10. The cavity of the guide vane 30 is used for the circulation of cool air, so as to cool the guide vane 30, the cool air enters the cooling flow channel 11 through the through hole 21, so as to cool the turbine casing 10, then the cool air enters the cavity of the guide vane 30 and is discharged through the air holes on the guide vane 30, so as to form a cooling film on the outer surface of the guide vane 30, and part of the cool air passes through the first stage working vane 60 and the second stage working vane 70.

In one embodiment, the inner surface of the turbine case 10 is provided with a thermal barrier coating 50. The thermal barrier coating 50 is used to insulate the combustion gas heat from reducing the temperature of the turbine case 10.

In one embodiment, the turbine nozzle is a one-piece, integrated structure formed by welding the nozzle vanes 30, the orifice ring 20, and the turbine casing 10 together as a one-piece structure. The guide vanes 30 are separately machined and welded by welding in the profile holes (weld grooves 12) of the turbine casing. The guide vane 30 is a cooling vane with an inner cavity, and a sealing sheet 40 is adopted between lower edge plates (free ends 312) of the guide vane 30 for sealing so as to reduce gas leakage. The orifice ring 20 is welded outside the turbine casing 10, and a narrow passage (cooling flow passage 11) is formed between the orifice ring 20 and the turbine casing 10 by impingement cooling through impingement holes (through holes 21), so that after the impingement of the cooling air, the flow velocity of the cooling air is increased in the narrow passage between the orifice ring 20 and the turbine casing 10, and the temperature of the turbine casing 10 is reduced. The cool air passes through the hole plate ring 20 to cool the turbine casing 10 and then enters the guide vanes 30 to cool the guide vanes 30, thereby improving the cool air utilization rate. The thermal barrier coating 50 is sprayed on the inner surface of the turbine casing 10, the temperature of the turbine casing 10 is reduced by isolating the heat of the combustion gas, the blade tip clearance is controlled, meanwhile, the turbine casing 10 is guaranteed to work in a tolerable temperature range, and the inner surface of the turbine casing 10 and the turbine rotor are matched to serve as a turbine outer ring. The guide blades 30 are cast cooling blades, the turbine casing 10 adopts low expansion alloy, such as a casting K423A, the expansion amount of the casing in a thermal state is reduced, and the blade tip clearance is controlled; and spraying a thermal barrier coating on the surface of the flow channel in the turbine casing.

The turbine guider is formed by welding the guide blades, the orifice plate ring and the turbine casing, integrates the function of the outer ring of the turbine, can effectively reduce the number of parts of the turbine, and has simple structure and high reliability; the integrated structure can reduce the assembly difficulty to the maximum extent, and has good assembly performance; the guide blade has a complex inner cavity and high casting difficulty, and the qualification rate of parts can be effectively ensured by single processing; an orifice plate ring is welded outside the turbine casing, small holes are punched on the orifice plate ring, cold air is used for cooling the surface of the turbine casing in an impact mode through the small holes, and meanwhile the casing is made of low-expansion alloy, so that the expansion amount of the thermal turbine casing is reduced, and the thermal tip clearance is controlled; after the cold air passes through the hole plate ring, the cold air enters the guide vanes to continue cooling the guide vanes, and the utilization rate of the cold air is effectively improved.

Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This invention is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and exemplary embodiments be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.

It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.

Claims

1. A turbine vane, comprising:

a turbine casing (10);

the turbine cooling structure comprises a hole plate ring (20), wherein the hole plate ring (20) is connected to the outer side of the turbine casing (10), a cooling flow channel (11) is arranged between the hole plate ring (20) and the turbine casing (10), and a through hole (21) communicated with the cooling flow channel (11) is formed in the hole plate ring (20);

-a guide vane (30), the guide vane (30) being connected to the inside of the turbine casing (10);

wherein the turbine case (10), the orifice ring (20), and the guide vanes (30) are of unitary construction.

2. The turbine guide of claim 1, wherein the orifice ring (20) is welded to the turbine case (10).

3. The turbine guide vane of claim 1, wherein the guide vane (30) is welded to the turbine casing (10).

4. The turbine vane as claimed in claim 3, characterized in that the guide vane (30) is a cast vane.

5. The turbine guide vane according to claim 3 or 4, characterized in that the guide vane (30) comprises a plurality of vane segments (31), the plurality of vane segments (31) being arranged one after the other in the circumferential direction of the turbine casing (10);

wherein a plurality of the blade segments (31) are formed independently.

6. The turbine guide according to claim 5, wherein the blade segment (31) comprises a welded end (311) and a free end (312), the welded end (311) is welded to the turbine casing (10), a reserved gap (32) is provided between two adjacent free ends (312), and the turbine guide further comprises:

a sealing sheet (40), wherein the sealing sheet (40) is arranged between two adjacent free ends (312) to seal the reserved gap (32).

7. The turbine guide vane according to claim 5, characterized in that a plurality of welding grooves (12) are provided on the turbine casing (10), the plurality of welding grooves (12) being provided in one-to-one correspondence with the plurality of blade segments (31);

wherein the welding end (311) of the blade segment (31) is arranged in the welding groove (12), the welding end (311) being adapted to the welding groove (12).

8. The turbine guide vane as claimed in claim 1, characterized in that the guide vane (30) has an inner cavity which communicates with the cooling flow channel (11), the inner cavity communicating with the inside of the turbine casing (10).

9. The turbine guide of claim 1, wherein the inner surface of the turbine casing (10) is provided with a thermal barrier coating (50).