A turbine guide vane endwall cooling test piece with slot and film independently replaceable

Abstract

The application discloses a turbine guide vane end wall cooling test piece with slot and air film capable of being independently replaced, which comprises an upper end wall and a lower end wall; the left side of the upper end wall is connected with a left wall surface, and the right side of the lower end wall is connected with a right wall surface; the upper end wall and the lower end wall are of the same structure, and the left wall surface and the right wall surface are of the same structure; the upper end wall and the lower end wall are both provided with an air film cooling structure and a slot cooling structure; the air film cooling structure and the slot cooling structure both have independent cooling cavities, and the air film cooling structure and the slot cooling structure are adjacent to each other and are provided with corresponding connecting holes. In the process of optimizing and testing the composite cooling structure of the turbine guide vane end wall, the cooling test piece can replace the single cooling structure, the processing and replacement of the single cooling structure can reduce the processing time and economic cost compared with the processing and replacement of the cooling structure of the whole end wall, and different cooling structures can be combined more flexibly.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine design, and particularly relates to a turbine guide vane end wall cooling test piece with independently replaceable slot and film. BACKGROUND

[0002] The turbine guide vane end wall of an aero-engine faces extremely high thermal load, and the continuously increasing turbine inlet temperature exposes the end wall to an environment higher than the melting point of the material for a long time, therefore, various cooling technologies need to be used to ensure the normal operation of the turbine guide vane end wall.

[0003] At present, there are two common cooling methods for the turbine guide vane end wall, namely turbine guide vane end wall film cooling and slot cooling.

[0004] Film cooling is to design film holes on the surface of the turbine guide vane end wall, and use the outflow of cold gas to form a film cover on the surface of the end wall to isolate the high-temperature gas from directly contacting the end wall, thereby protecting the end wall.

[0005] Slot cooling is to use the cold gas at the joint of the combustion chamber-turbine to cool the surface of the turbine guide vane end wall.

[0006] However, it is difficult to achieve full coverage of the end wall by the cold gas using a single cooling structure, in order to improve the cooling effect of the end wall, a composite cooling structure is proposed. The design of a composite cooling structure inevitably needs to be iterated and tested for multiple rounds, and the prior art generally designs the end wall as a whole, that is, the composite cooling structure of the end wall is processed as a whole, and in the experimental process, if one of the composite cooling structures needs to be replaced, the entire test piece needs to be reprocessed, which means that each time one of the cooling structures needs to be optimized, additional time and economic cost of processing the test piece of the other part of the end wall are required.

[0007] Therefore, based on the above technical problems, the person skilled in the art urgently needs to develop a turbine guide vane end wall cooling test piece with independently replaceable slot and film. SUMMARY

[0008] The purpose of the present application is to provide a turbine guide vane end wall cooling test piece with independently replaceable slot and film, which has a split structure to help reduce the processing time and economic cost required when replacing one of the cooling structures during the test process of the composite cooling structure.

[0009] In order to achieve the above purpose, the present application provides the following technical scheme:

[0010] The turbine guide vane end wall cooling test piece with independent replacement of the slot and the air film comprises an upper end wall and a lower end wall;

[0011] The left wall surface is connected to the left side of the upper end wall, and the right wall surface is connected to the right side of the lower end wall;

[0012] The upper end wall and the lower end wall are of the same structure, and the left wall surface and the right wall surface are of the same structure;

[0013] The upper end wall and the lower end wall are both provided with air film cooling structures and slot cooling structures, wherein the air film cooling structures and the slot cooling structures each have independent cooling cavities, and the air film cooling structures and the slot cooling structures are adjacent to each other and avoid being provided with corresponding connecting holes;

[0014] The upper end wall and the lower end wall, the upper end wall and the left wall surface, and the lower end wall and the right wall surface are fixed by step surfaces.

[0015] Further, the right wall surface connecting flange is arranged at the position where the right wall surface is connected to the lower end wall;

[0016] The wall surface blade-shaped protrusion is formed on the inner surface of the right wall surface.

[0017] Further, the lower end wall step matching surface and the lower end wall connecting right wall surface flange are formed at the position where the lower end wall cooperates with the right wall surface;

[0018] The right wall surface connecting flange of the right wall surface cooperates with the lower end wall connecting right wall surface flange of the lower end wall to realize the positioning connection of the right wall surface and the lower end wall.

[0019] Further, the air film cooling structure and the slot cooling structure are integrated in the lower end wall close to each other;

[0020] The lower end wall is fixed by the corresponding connecting flanges to assemble the air film cooling structure and the slot cooling structure.

[0021] Further, the lower end wall and the air film cooling structure and the slot cooling structure are matched to form a step assembly surface, and the lower end wall is respectively provided with an air film connecting flange connected to the connecting flange of the air film cooling structure and a slot connecting flange connected to the connecting flange of the slot cooling structure.

[0022] Further, the lower end wall slot end cover is arranged at the connection between the slot cooling structure and the slot connecting flange;

[0023] The air film cooling structure and the slot cooling structure are both extended with a cold air inlet pipe, and an air film end cover is installed at the end of the cold air inlet pipe of the air film cooling structure.

[0024] Further, the part of the cold air inlet pipe extending into the corresponding cooling cavity is formed as a honeycomb flow resistance structure.

[0025] Further, the position of the cooling structure of the lower end wall and the upper end wall can be replaced by an observation plate.

[0026] Further, the mounting structure of the upper end wall and the left wall surface is the same as the mounting structure of the lower end wall and the right wall surface.

[0027] The mounting structure of the upper end wall and the air film cooling structure and the slot cooling structure is the same as the mounting structure of the lower end wall and the air film cooling structure and the slot cooling structure.

[0028] In the above technical solution, the turbine guide vane end wall cooling test piece with independent replaceable slot and air film has the following beneficial effects:

[0029] The cooling test piece can replace the single cooling structure during the optimization and test of the turbine guide vane end wall composite cooling structure, and the processing and replacement of the single cooling structure reduces the processing time and economic cost compared with the processing and replacement of the overall end wall cooling structure, and different cooling structures can be combined more flexibly.

[0030] The structure design method can observe the experimental effect inside the blade passage through the observation plate without affecting the flow channel of the test piece. BRIEF DESCRIPTION OF DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0032] Figure 1 The test piece flow channel schematic diagram of the turbine guide vane end wall cooling test piece with independent replaceable slot and air film disclosed by the embodiment of the present application is shown in the figure;

[0033] Figure 2 The right wall surface inner wall surface blade-shaped protrusion schematic diagram of the turbine guide vane end wall cooling test piece with independent replaceable slot and air film disclosed by the embodiment of the present application is shown in the figure;

[0034] Figure 3A structure schematic view of a lower end wall step matching surface of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0035] Figure 4 A composite cooling structure schematic view of a lower end wall of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0036] Figure 5 A structure schematic view of an air film cooling cavity of an air film cooling structure of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0037] Figure 6 A structure schematic view of a slot cooling cavity of a slot cooling structure of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0038] Figure 7 A lower end wall and cooling structure connecting step assembly structure of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0039] Figure 8 An air film cavity end cover schematic view of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application;

[0040] Figure 9 A lower end wall cooling structure observation effect schematic view of a slot and air film independently replaceable turbine guide vane end wall cooling test piece disclosed by the embodiment of the present application.

[0041] BRIEF DESCRIPTION OF THE DRAWINGS

[0042] 1, upper end wall; 2, lower end wall; 3, left wall surface; 4, right wall surface; 5, right wall surface connecting flange; 6, wall surface leaf-shaped protrusion; 7, lower end wall step matching surface; 8, lower end wall connecting right wall surface flange; 9, air film cooling structure; 10, slot cooling structure; 11, lower end wall air film end cover; 12, lower end wall slot end cover; 13, air film cooling cavity connecting hole; 14, slot cooling cavity connecting hole; 15, step assembly surface; 16, slot connecting flange; 17, air film connecting flange; 18, honeycomb flow resistance structure; 19, cold gas inlet; 20, slot observation plate; 21, air film observation plate. DETAILED DESCRIPTION

[0043] In order for those skilled in the art to better understand the technical solutions of the present application, the present application will be further described in detail below with reference to the drawings.

[0044] Referring to Figures 1 to 9 the drawings;

[0045] The turbine guide vane end wall cooling test piece of the embodiment has a slot and a gas film which can be replaced independently, and the end wall cooling test piece comprises an upper end wall 1 and a lower end wall 2;

[0046] The left wall surface 3 is connected to the left side of the upper end wall 1, and the right wall surface 4 is connected to the right side of the lower end wall 2;

[0047] The upper end wall 1 and the lower end wall 2 have the same structure, and the left wall surface 3 and the right wall surface 4 have the same structure;

[0048] The upper end wall 1 and the lower end wall 2 are both provided with a gas film cooling structure 9 and a slot cooling structure 10, wherein the gas film cooling structure 9 and the slot cooling structure 10 each have a cooling cavity which is independent of each other, and the gas film cooling structure 9 and the slot cooling structure 10 are adjacent to each other and avoid being provided with a corresponding connecting hole;

[0049] The upper end wall 1 and the lower end wall 2, the upper end wall 1 and the left wall surface 3, and the lower end wall 2 and the right wall surface 4 are all fixed by positioning and assembling through a stepped surface.

[0050] Secondly, the mounting structure of the upper end wall 1 and the left wall surface 3 of the embodiment is the same as the mounting structure of the lower end wall 2 and the right wall surface 4, and the mounting structure of the upper end wall 1 and the gas film cooling structure 9 and the slot cooling structure 10 is the same as the mounting structure of the lower end wall 2 and the gas film cooling structure 9 and the slot cooling structure 10.

[0051] Therefore, the structure of one side of the lower end wall 2 and the connection relationship of the structure are further explained and described, so as to limit the upper end wall 1 and the lower end wall 2.

[0052] Referring to Figure 2 Preferably, the position where the right wall surface 4 of the embodiment is connected to the lower end wall 2 is provided with a right wall surface connecting flange 5, and the inner side surface of the right wall surface 4 is protruded to form a wall surface leaf-shaped protrusion 6. Referring to Figure 5 and Figure 6 Firstly, the gas film cooling structure 9 and the slot cooling structure 10 of the embodiment each have a cooling cavity which is independent of each other, and the gas film cooling structure 9 and the slot cooling structure 10 are adjacent to each other and avoid being provided with a corresponding connecting hole; the two independent cooling structures are connected through bolts to ensure the air tightness of the composite structure.

[0053] Referring to Figure 2 and Figure 3 Preferably, the position where the lower end wall 2 of the embodiment cooperates with the right wall surface 4 forms a lower end wall stepped cooperation surface 7 and a lower end wall connecting right wall surface flange 8 located on the side surface of the lower end wall stepped cooperation surface 7; firstly, Figure 2The right wall surface 4 of the embodiment is shown in the figure, which has a right wall surface connecting flange 5 and a wall surface lobe-shaped protrusion 6 formed on the side surface. Based on this, the right wall surface connecting flange 5 of the right wall surface 4 of the embodiment cooperates with the lower end wall connecting right wall surface flange 8 to realize the positioning connection of the right wall surface 4 and the lower end wall 2.

[0054] Referring to Figure 4 As shown in the figure, preferably, the gas film cooling structure 9 and the slot cooling structure 10 of the embodiment are integrated close to each other on the lower end wall 2.

[0055] The lower end wall 2 is respectively assembled and fixed with the gas film cooling structure 9 and the slot cooling structure 10 through corresponding connecting flanges.

[0056] Specifically, referring to Figure 7 As shown in the figure, the matching position of the lower end wall 2 and the gas film cooling structure 9 and the slot cooling structure 10 of the embodiment is formed as a stepped assembly surface 15, and the lower end wall 2 is respectively provided with a gas film connecting flange 17 connected with the connecting flange of the gas film cooling structure 9 and a slot connecting flange 16 connected with the connecting flange of the slot cooling structure 10.

[0057] In addition, referring to Figure 4 and Figure 7 As shown in the figure, the slot cooling structure 10 of the embodiment is provided with a lower end wall slot end cover 12 at the connection with the slot connecting flange 16; the gas film cooling structure 9 and the slot cooling structure 10 are both protrudingly extended with a cold gas inlet pipe, and the end of the cold gas inlet pipe of the gas film cooling structure 9 is installed with a gas film end cover 11.

[0058] Referring to Figure 8 As shown in the figure, the part of the cold gas inlet pipe extended into the corresponding cooling cavity is formed as a honeycomb flow resistance structure 18.

[0059] The cooling structure and the end wall structure of the embodiment are connected through the flange structure, and the positioning accuracy and the good air tightness when the cooling structure and the end wall structure are connected are ensured through the mutual cooperation between the stepped assembly structure and the flange assembly structure.

[0060] In order to better observe the test and the specific situation inside the blade passage of the test piece, the position where the cooling structure of the lower end wall 2 cooperates with the upper end wall 1 of the embodiment can be replaced with an observation plate to replace the cooling structure of the upper end wall.

[0061] The observation plate is divided into a slot observation plate 20 and a gas film observation plate 21.

[0062] In the above technical solution, the turbine guide vane end wall cooling test piece with the slot and the gas film being independently replaceable provided by the application has the following beneficial effects:

[0063] The cooling test piece of the present application can be replaced for a single cooling structure in the optimization and test process of the turbine guide vane end wall composite cooling structure, and the machining and replacement of the single cooling structure reduces the machining time and economic cost relative to the machining and replacement of the overall end wall cooling structure, and different cooling structures can be combined more flexibly.

[0064] The structural design method of the present application can observe the experimental effect inside the blade channel through the observation plate without affecting the flow channel of the test piece.

[0065] The above only describes certain exemplary embodiments of the present application by way of illustration, and it is needless to say that the described embodiments can be modified in various ways without departing from the spirit and scope of the present application for those skilled in the art. Therefore, the above drawings and descriptions are illustrative in nature and should not be understood as limiting the scope of protection of the claims of the present application.

Claims

1. A turbine guide vane endwall cooling test piece with independently replaceable slots and film, characterized by, The end wall cooling test piece comprises an upper end wall (1) and a lower end wall (2); The left wall surface (3) is connected to the left side of the upper end wall (1), and the right wall surface (4) is connected to the right side of the lower end wall (2); The upper end wall (1) and the lower end wall (2) have the same structure, and the left wall surface (3) and the right wall surface (4) have the same structure; The upper end wall (1) and the lower end wall (2) are both provided with a film cooling structure (9) and a slot cooling structure (10), wherein the film cooling structure (9) and the slot cooling structure (10) each have a cooling cavity independent of each other, and the film cooling structure (9) and the slot cooling structure (10) are adjacent to each other and avoid being provided with a corresponding connecting hole; The upper end wall (1) and the lower end wall (2) are fixed by step positioning assembly between the upper end wall (1) and the left wall surface (3) and between the lower end wall (2) and the right wall surface (4).

2. The slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece of claim 1, wherein, The right wall surface (4) is provided with a right wall surface connecting flange (5) at the position connected to the lower end wall (2); The right wall surface (4) is provided with a wall surface leaf-shaped protrusion (6) protruding from the inner side surface.

3. The slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece of claim 2, wherein, The lower end wall (2) is provided with a lower end wall step matching surface (7) and a lower end wall connecting right wall surface flange (8) at the position matched with the right wall surface (4); The right wall surface connecting flange (5) of the right wall surface (4) is matched with the lower end wall connecting right wall surface flange (8) to realize the positioning connection of the right wall surface (4) and the lower end wall (2).

4. The slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece of claim 3, wherein, The film cooling structure (9) and the slot cooling structure (10) are integrated close to each other in the lower end wall (2); The lower end wall (2) is provided with a film connecting flange (17) connected to the connecting flange of the film cooling structure (9) and a slot connecting flange (16) connected to the connecting flange of the slot cooling structure (10) through the corresponding connecting flanges.

5. The slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece of claim 4, wherein, The slot cooling structure (10) is provided with a lower end wall slot end cover at the connection position of the slot connecting flange (16).

6. A slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece according to claim 5, wherein The film cooling structure (9) and the slot cooling structure (10) are both provided with a cold gas inlet pipe protruding and extending, and the end of the cold gas inlet pipe of the film cooling structure (9) is provided with a film end cover (11). The part of the cold gas inlet pipe extending into the corresponding cooling cavity is formed as a honeycomb flow resistance structure (18).

7. The slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece of claim 6, wherein, The position of the lower end wall (2) matched with the cooling structure of the upper end wall (1) can replace the cooling structure of the upper end wall (1) through an observation plate.

8. The slotted and airfoil independently replaceable turbine guide vane endwall cooling insert of claim 5, wherein, The installation structure of the upper end wall (1) and the left wall surface (3) is the same as the installation structure of the lower end wall (2) and the right wall surface (4).

9. A slotted and airfoil independently replaceable turbine guide vane endwall cooling test piece according to any one of claims 1-8, wherein, ​ The mounting structure of the upper end wall (1) and the film cooling structure (9) and the slot cooling structure (10) is the same as the mounting structure of the lower end wall (2) and the film cooling structure (9) and the slot cooling structure (10).

Images