High-temperature cold effect test device and test method

Abstract

The application discloses a high-temperature cold effect test device and a test method. The test device comprises a flow channel structure, an installation structure, an air inlet connecting structure and an air outlet connecting structure. The flow channel structure has an inner flow channel and is matched with a gas flow passage of an engine. The flow channel structure comprises an inner layer wall and an outer layer wall. An inner cavity of the inner layer wall is the inner flow channel. A sandwich cavity is formed between the inner layer wall and the outer layer wall. A water inlet structure is arranged at an inlet end of the flow channel structure and is used for guiding the cooling liquid into the sandwich cavity. A water outlet structure is arranged at an outlet end of the flow channel structure and is used for guiding the cooling liquid in the sandwich cavity out. The installation structure is arranged on the flow channel structure and is used for installing a blade assembly. The air inlet connecting structure is arranged at the inlet end of the flow channel structure and is used for being connected with an outlet end of a fuel heater of a test vehicle. The air outlet connecting structure is arranged at the outlet end of the flow channel structure and is used for being connected with an exhaust pipe.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbine blade cooling effect test of an aero-engine, and particularly relates to a high-temperature cooling effect test device. In addition, the present application also relates to a test method comprising the high-temperature cooling effect test device. BACKGROUND

[0002] With the development of aero-engine technology, performance parameters such as the thrust-to-weight ratio, the turbine inlet temperature and the total pressure ratio of the engine are significantly improved. Research shows that, without changing the size of the engine, the cycle thermal efficiency of the aero-gas turbine engine can be increased by 2% to 4% and the thrust can be increased by 8% to 13% when the turbine inlet temperature is increased by 56℃. At present, the turbine inlet temperature of an advanced aero-engine has reached 1800K to 2000K, and the inlet temperature of the turbine blade of the next generation engine is expected to reach 2000K to 2250K, which is far beyond the limit temperature of the material, and various advanced cooling structures are needed to ensure the reliable work of the turbine blade. Therefore, in the design process of the turbine component, a large amount of testing and testing needs to be carried out, and the flow and heat exchange of the developed engine turbine blade and each typical component need to be researched and verified in detail, so as to effectively guide the design.

[0003] The turbine blade cooling effect test is the basis for verifying the heat transfer and fluid dynamics design of the turbine blade and is an important verification means for scheme design. Considering the material temperature resistance limit and the manufacturing cost, the existing aero-engine turbine blade cooling effect test device has a simple overall structure, mainly carries out turbine blade cooling effect test under a medium-temperature and medium-pressure environment, models the engine working condition to the medium-temperature and medium-pressure condition through similarity criteria, and calculates the cooling performance of the turbine blade under the real engine environment by measuring parameters such as the main gas flow, pressure and temperature, the cold gas flow, pressure and temperature, and the blade surface temperature. However, compared with the medium-temperature and medium-pressure environment, in the real engine environment with high temperature and high pressure, the gas in the flow passage of the turbine component has higher radiation heat and more intense turbulence, and the gas property parameters differ greatly between high temperature and medium temperature, which cannot be simulated in the medium-temperature and medium-pressure environment. The engine turbine blade cooling effect test under the medium-temperature and medium-pressure simulated environment cannot completely verify the performance and use results of the blade under the real engine environment. SUMMARY

[0004] The present application provides a high-temperature cooling effect test device and a test method, to solve the technical problems of great difficulty in simulating the real environment working condition and high cost in the blade cooling effect test under high temperature and high pressure conditions.

[0005] According to one aspect of the present application, a high-temperature cooling effect test device is provided, which is applied to the turbine blade cooling effect test of an aero-engine, and the test device comprises:

[0006] The flow channel structure has an inner flow channel configured to match a fuel gas flow passage of an engine. The flow channel structure includes an inner layer wall and an outer layer wall. An inner cavity of the inner layer wall is the inner flow channel. A sandwich cavity is formed between the inner layer wall and the outer layer wall. An inlet end of the flow channel structure is provided with a water inlet structure for guiding the cooling liquid into the sandwich cavity. An outlet end of the flow channel structure is provided with a water outlet structure for guiding the cooling liquid out of the sandwich cavity.

[0007] The mounting structure is arranged on the flow channel structure and is used for mounting the vane assembly.

[0008] The air inlet connecting structure is arranged at the inlet end of the flow channel structure and is used for connecting with the outlet end of the fuel heater of the test bench.

[0009] The exhaust connecting structure is arranged at the outlet end of the flow channel structure and is used for connecting with the exhaust pipe.

[0010] As a further improvement of the above technical solution, the air inlet connecting structure includes an air inlet flange arranged at the air inlet end of the flow channel structure. The water inlet structure is arranged on the outer layer wall close to the air inlet flange.

[0011] As a further improvement of the above technical solution, the water inlet structure includes a water inlet opening arranged on the outer layer wall at a preset incident angle, so that the cooling liquid is sprayed to the end surface of the air inlet flange. Two or more water inlet openings are uniformly distributed in the circumferential direction.

[0012] As a further improvement of the above technical solution, the exhaust connecting structure includes an exhaust flange arranged at the outlet end of the flow channel structure. The water outlet structure includes a plurality of drainage holes uniformly arranged in the circumferential direction. The water outlet structure is connected to the exhaust pipe, so that the discharged cooling liquid is mixed with the high-temperature fuel gas discharged from the flow channel structure and is discharged through the exhaust pipe.

[0013] As a further improvement of the above technical solution, the flow area of the water inlet structure matches the flow area of the water outlet structure.

[0014] As a further improvement of the above technical solution, the sandwich cavity is provided with a turbulence support structure connected to the inner layer wall and the outer layer wall, respectively.

[0015] As a further improvement of the above technical solution, the flow channel structure is provided with a first mounting seat and a second mounting seat, respectively used for mounting a total pressure probe and a total temperature probe.

[0016] As a further improvement of the above technical solution, graphite gaskets are arranged between the total pressure probe and the first mounting seat and between the total temperature probe and the second mounting seat, respectively.

[0017] As a further improvement of the above technical solution, the vane assembly comprises a cooling vane and a vane mounting seat connected with the mounting structure, and the vane mounting seat has a mounting structure matched with the shape of the cooling vane.

[0018] According to another aspect of the present application, there is also provided a test method comprising the high-temperature cold effect test device.

[0019] The present application has the following advantages:

[0020] The inlet connection structure at the end of the test device is connected with the outlet of the fuel heater of the test vehicle platform, the fuel heater provides high-temperature and high-pressure fuel gas into the inner flow channel structure consistent with the actual working state of the engine, and the structure of the inner flow channel is consistent with the actual shape and size of the engine fuel gas flow channel, and the temperature, pressure and the like of the inlet fuel gas are consistent with the actual environmental conditions of the engine; the double-wall structure is provided to form a sandwich cavity and introduce cooling liquid to cool and cool the flow channel structure of the high-temperature and high-pressure fuel gas, the cooling liquid flows in the sandwich cavity along the fuel gas flow direction, and is discharged through the water outlet structure at the outlet end to realize cooling and heat exchange of the flow channel structure, the temperature of the fuel gas in the flow channel exceeds 1200℃, and ordinary metal materials are difficult to work reliably at such a high temperature, but based on the structure of the test device, the sandwich cavity formed by the double-wall structure introduces cooling liquid for heat exchange, and ordinary stainless steel materials can be used to manufacture the test device to realize the cold effect test of the turbine blade in the high-temperature and high-pressure real environment, thereby greatly saving the cost, and the cooling effect of the turbine blade can be truly verified to improve the accuracy of the turbine test verification result and effectively calibrate and correct the design of the turbine cooling vane.

[0021] In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. The present application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0022] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate preferred embodiments of the present application, and assist in the explanation of the present application. In the drawings:

[0023] Fig. 1 is a structural schematic diagram of a preferred embodiment of the present application;

[0024] Fig. 2 is a cross-sectional view of the flow channel structure of a preferred embodiment of the present application;

[0025] Fig. 3 is a schematic diagram of a probe mounting structure of a preferred embodiment of the present application.

[0026] LEGEND:

[0027] 1, flow channel structure; 11, inner layer wall; 2, outer layer wall; 13, inner flow channel; 14, interlayer cavity; 15, water inlet structure; 16, water outlet structure; 17, mounting structure; 18, turbulence support structure; 2, cooling vane; 21, cooling bleed air structure; 22, vane mounting seat; 3, air inlet connecting structure; 4, air outlet connecting structure; 5, water inlet joint; 6, first mounting seat; 7, second mounting seat; 8, total pressure probe; 9, total temperature probe; 10, graphite gasket. DETAILED DESCRIPTION

[0028] The embodiments of the present application will be described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following.

[0029] Fig. 1 is a structural schematic diagram of a preferred embodiment of the present application; Fig. 2 is a cross-sectional view of the flow channel structure of the preferred embodiment of the present application; Fig. 3 is a schematic diagram of the probe mounting structure of the preferred embodiment of the present application.

[0030] As shown in Figs. 1 to 3 , the high-temperature cooling effect test device of the present embodiment is applied to the cooling effect test of the turbine vane of an aero-engine, and the test device comprises:

[0031] The flow channel structure 1 has an inner flow channel 13, which is configured to match the gas flow passage of the engine; the flow channel structure 1 comprises an inner layer wall 11 and an outer layer wall 12, the inner cavity of the inner layer wall 11 is the inner flow channel 13, and an interlayer cavity 14 is formed between the inner layer wall 11 and the outer layer wall 12; a water inlet structure 15 is arranged at the inlet end of the flow channel structure 1, for guiding the cooling liquid into the interlayer cavity 14; and a water outlet structure 16 is arranged at the outlet end of the flow channel structure 1, for guiding the cooling liquid in the interlayer cavity 14 out;

[0032] The mounting structure 17 is arranged on the flow channel structure 1, for mounting the vane assembly;

[0033] The air inlet connecting structure 3 is arranged at the inlet end of the flow channel structure 1, for connecting with the outlet end of the fuel heater of the test bench;

[0034] The air outlet connecting structure 4 is arranged at the outlet end of the flow channel structure 1, for connecting with the exhaust pipe.

[0035] The blade assembly includes a cooling blade 2 to be tested, which is designed with a cooling bleed air structure 21 and a cold air passage structure. The surface temperature of the metal blade is measured by a thermocouple measurement point arranged on the surface of the cooling blade 2 to obtain the cooling effect characteristics of the blade surface. The blade assembly further includes a blade mounting seat 22 connected to the mounting structure 17. The blade mounting seat 22 has a mounting structure matched with the shape of the cooling blade 2. The mounting structure of the blade mounting seat 22 is designed according to different models and structures of the cooling blade 2. The blade mounting seat 22 is fastened and connected to the mounting structure 17 by bolts. The cooling blade 2 is inserted into the mounting structure into the inner flow channel 13. The cooling bleed air structure 21 (such as a bleed air joint) at the root of the cooling blade 2 is connected to an external air source.

[0036] It can be understood that the air inlet connection structure 3 at the end of the test device is connected to the outlet of the test vehicle fuel warmer. The fuel warmer provides high-temperature and high-pressure gas consistent with the actual working state of the engine into the inner flow channel 13 of the flow channel structure 1. The structure of the inner flow channel 13 is consistent with the actual shape and size of the engine gas flow channel. The temperature, pressure, and other parameters of the gas entering are consistent with the actual working conditions of the engine. The flow channel structure 1 with high-temperature and high-pressure gas is cooled by the double-wall structure forming the interlayer cavity 14 and introducing cooling liquid. The cooling liquid flows in the interlayer cavity 14 along the direction of the gas flow and is discharged from the water outlet structure 16 at the outlet end. The cooling and heat exchange of the flow channel structure 1 are realized. The temperature of the gas in the flow channel exceeds 1200℃, and ordinary metal materials are difficult to work reliably at such high temperatures. Based on the structure of the test device, the interlayer cavity 14 formed by the double-wall structure introduces cooling liquid for heat exchange. The test device made of ordinary stainless steel material can be used to realize the cooling effect test of turbine blades in high-temperature and high-pressure real environment, greatly saving the cost, and truly verifying the cooling effect of turbine blades, improving the accuracy of turbine test verification results, and effectively calibrating and correcting the design of turbine cooling blades 2.

[0037] The shell of the flow channel structure 1 is integrally formed by additive manufacturing, avoiding the problems of double-shell mechanical machining and welding difficulties, and having good high-temperature resistance.

[0038] In this embodiment, the air inlet connection structure 3 includes an air inlet flange arranged at the air inlet end of the flow channel structure 1. The water inlet structure 15 is arranged on the outer wall 12 near the air inlet flange, and the water inlet connector 5 is arranged to connect with the water inlet pipeline, without affecting the disassembly and connection of the bolts on the air inlet flange.

[0039] Further, the water inlet structure 15 includes a water inlet opening provided on the outer wall 12 at a preset incident angle, so that the cooling liquid is sprayed to the air inlet flange end face. By arranging the water inlet opening on the outer wall 12 close to the air inlet flange and at a preset angle, effective cooling of the air inlet flange by the cooling liquid is achieved while avoiding affecting the disassembly of the bolts on the air inlet flange; two or more water inlet openings are uniformly distributed circumferentially.

[0040] In this embodiment, the exhaust connection structure 4 includes an exhaust flange arranged at the outlet end of the flow channel structure 1, and the water outlet structure 16 is connected to the exhaust pipe for mixing the discharged cooling liquid with the high-temperature gas discharged from the flow channel structure 1 and discharging the mixed gas through the exhaust pipe. The discharged cooling liquid is mixed with the high-temperature gas discharged from the flow channel structure 1, thereby cooling the discharged high-temperature gas, so that the exhaust pipe can also be made of ordinary metal materials to achieve exhaust, greatly reducing the cost of the device; the water outlet structure 16 includes a plurality of drainage holes arranged uniformly in a ring shape, which has a structure similar to the water outlet holes of a shower flower, greatly improving the uniformity of the mixing of the discharged cooling water and the high-temperature gas, maximizing the efficiency of the cooling liquid, and greatly improving the cooling effect and reducing the gas temperature.

[0041] It should be understood that the flow area of the water inlet structure 15 matches the flow area of the water outlet structure 16, i.e., the total area of the water inlet holes is equal to the total area of the drainage holes, so as to avoid liquid deficiency in the interlayer cavity 14 and ensure the heat exchange effect;

[0042] In this embodiment, the interlayer cavity 14 is provided with a turbulence support structure 18 connected to the inner wall 11 and the outer wall 12, the turbulence support structure 18 includes a plurality of groups of reinforcing ribs arranged along the length extension direction of the flow channel structure 1, each group of reinforcing ribs includes a plurality of reinforcing ribs uniformly distributed circumferentially, the reinforcing ribs can support and connect the inner wall 11 and the outer wall 12, and at the same time, the reinforcing ribs can disturb the flow of the cooling liquid to improve the heat exchange effect of the cooling liquid; the shape of the reinforcing ribs can be designed as a cylinder, a rhombus, a water drop, etc., and preferably, the reinforcing ribs with appropriate shapes are designed based on simulation calculation.

[0043] In this embodiment, the flow channel structure 1 is provided with a first mounting seat 6 and a second mounting seat 7 for mounting a total pressure probe 8 and a total temperature probe 9, respectively, and the total pressure probe 8 and the total temperature probe 9 are used to measure the pressure and temperature of the inner flow channel 13; the total pressure probe 8, the total temperature probe 9, and the blade assembly are all detachable structures, so that they can be replaced when damaged, and different types and specifications of cooling tests can be adapted according to test requirements.

[0044] In the embodiment, graphite gaskets 10 are arranged between the total pressure probe 8 and the first mounting seat 6 and between the total temperature probe 9 and the second mounting seat 7, and graphite gaskets 10 are also arranged at the matching parts of the vane assembly, so as to realize sealing and prevent gas leakage of the inner flow channel 13. The graphite gaskets 10 have good high-temperature resistance and can adapt to the test environment.

[0045] The preferred embodiments of the present application have been described above with reference to the drawings, but the present application is not limited to the above examples, and various modifications and changes can be made by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A high-temperature cooling effect testing device, used for testing the cooling effect of aero-engine turbine blades, characterized in that, The test apparatus includes: The flow channel structure (1) has an inner flow channel (13) and is configured to match the gas flow channel of the engine. The flow channel structure (1) includes an inner wall (11) and an outer wall (12). The inner cavity of the inner wall (11) is the inner flow channel (13). An interlayer cavity (14) is formed between the inner wall (11) and the outer wall (12). The inlet end of the flow channel structure (1) is provided with a water inlet structure (15) for introducing coolant into the interlayer cavity (14). The outlet end of the flow channel structure (1) is provided with a water outlet structure (16) for discharging coolant from the interlayer cavity (14). Mounting structure (17) is provided on the flow channel structure (1) for mounting blade assembly; The intake connection structure (3) is located at the inlet end of the flow channel structure (1) and is used to connect to the outlet end of the fuel heater of the test vehicle platform. An exhaust connection structure (4) is provided at the outlet end of the flow channel structure (1) for connecting to an exhaust pipe; the exhaust connection structure (4) includes an exhaust flange provided at the outlet end of the flow channel structure (1), and the water outlet structure (16) includes a plurality of drainage holes evenly distributed along the circumference. The water outlet structure (16) is connected to the exhaust pipe for mixing the discharged coolant with the high-temperature gas discharged from the flow channel structure (1) and discharging it through the exhaust pipe to cool the discharged high-temperature gas, so that the exhaust pipe can achieve exhaust based on ordinary metal materials.

2. The high-temperature cooling effect testing device according to claim 1, characterized in that, The air intake connection structure (3) includes an air intake flange disposed at the air intake end of the flow channel structure (1), and the water intake structure (15) is disposed on the outer wall (12) near the air intake flange.

3. The high-temperature cooling effect testing device according to claim 2, characterized in that, The water inlet structure (15) includes a water inlet at a preset incident angle on the outer wall (12) so that coolant is sprayed onto the air intake flange end face; two or more water inlets are evenly distributed circumferentially.

4. The high-temperature cooling effect testing apparatus according to any one of claims 1-3, characterized in that, The flow area of ​​the water inlet structure (15) matches the flow area of ​​the water outlet structure (16).

5. The high-temperature cooling effect testing device according to claim 1, characterized in that, The interlayer cavity (14) is provided with a turbulence support structure (18), which is connected to the inner wall (11) and the outer wall (12).

6. The high-temperature cooling effect testing device according to claim 1, characterized in that, The flow channel structure (1) is provided with a first mounting base (6) and a second mounting base (7), which are used to install the total pressure probe (8) and the total temperature probe (9), respectively.

7. The high-temperature cooling effect testing device according to claim 6, characterized in that, Graphite gaskets (10) are respectively provided between the total pressure probe (8) and the first mounting base (6) and between the total temperature probe (9) and the second mounting base (7).

8. The high-temperature cooling effect testing device according to claim 1, characterized in that, The blade assembly includes a cooling blade (2) and a blade mounting base (22) connected to the mounting structure (17), the blade mounting base (22) having a mounting configuration that matches the shape of the cooling blade (2).

9. A test method, characterized in that, The application has the high-temperature cooling effect test device as described in any one of claims 1-8.

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