High-temperature cooling effect test device and test method

Abstract

The invention discloses a high-temperature cooling effect test device and method, and the device comprises a flow channel structure which is provided with an inner flow channel and is configured to be matched with a fuel gas circulation channel 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 an inner flow channel, an interlayer cavity is formed between the inner layer wall and the outer layer wall, a water inlet structure is arranged at the inlet end of the flow channel structure and used for guiding cooling liquid into the interlayer cavity, and a water outlet structure is arranged at the outlet end of the flow channel structure and used for guiding out the cooling liquid in the interlayer cavity. The mounting structure is arranged on the flow channel structure and is used for mounting the 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 the outlet end of a fuel oil heater of a test vehicle platform; and the exhaust connecting structure is arranged at the outlet end of the flow channel structure and used for being connected with an exhaust pipeline.

Description

Technical Field

[0001] This invention relates to the field of testing technology for the cooling effect of aero-engine turbine blades, and in particular, to a high-temperature cooling effect testing apparatus. Furthermore, this invention also relates to a testing method comprising the aforementioned high-temperature cooling effect testing apparatus. Background Art

[0002] With the development of aero-engine technology, performance parameters such as thrust-to-weight ratio, turbine inlet temperature, and overall pressure ratio have been significantly improved. Studies show that, without changing engine size, an increase of 56°C in turbine inlet temperature can increase the cycle thermal efficiency of an aero-gas turbine engine by 2%–4% and thrust by approximately 8%–13%. Currently, the turbine inlet temperature of advanced aero-engines has reached 1800K–2000K, and the expected turbine blade inlet temperature of the next generation of engines may even reach 2000–2250K, far exceeding the material's temperature limit. This necessitates various advanced cooling structures to ensure the reliable operation of the turbine blades. Therefore, extensive testing and experimentation are required during turbine component design to conduct in-depth and detailed research and verification of the flow and heat transfer of the developed engine turbine blades and various typical components, thereby effectively guiding the design process.

[0003] Turbine blade cooling effect testing is fundamental to verifying the heat transfer and hydrodynamic design of turbine blades and is an important verification method for scheme design. Considering material temperature resistance limitations and manufacturing costs, existing aero-engine turbine blade cooling effect testing devices have a simple overall structure. They mainly conduct turbine blade cooling effect tests under medium-temperature and medium-pressure environments, simulating engine operating conditions to medium-temperature and medium-pressure conditions using similarity criteria. The cooling performance of turbine blades under real engine conditions is estimated by measuring parameters such as main gas flow rate, pressure, and temperature, coolant flow rate, pressure, and temperature, and blade surface temperature. However, compared to the medium-temperature and medium-pressure environment, the combustion gases in the turbine component flow channels have higher radiant heat and more intense turbulence under the real high-temperature and high-pressure engine environment. Furthermore, the gas physical properties differ significantly between high and medium temperatures. These effects cannot be simulated under the medium-temperature and medium-pressure environment. Therefore, conducting turbine blade cooling effect tests under simulated medium-temperature and medium-pressure environments cannot fully verify the performance and usage results of the blades under real engine conditions. Summary of the Invention

[0004] This invention provides a high-temperature cooling effect testing device and method to solve the technical problems of high difficulty and high cost in simulating real environmental conditions due to the limitation of high temperature and high pressure in blade cooling effect testing.

[0005] According to one aspect of the present invention, a high-temperature cooling effect testing apparatus is provided for testing the cooling effect of turbine blades in aero-engines. The testing apparatus includes:

[0006] The flow channel structure has an inner flow channel, and its construction is matched with the gas flow passage of the engine. The flow channel structure includes an inner wall and an outer wall. The inner cavity of the inner wall is the inner flow channel. An interlayer cavity is formed between the inner wall and the outer wall. The inlet end of the flow channel structure is provided with a water inlet structure for introducing coolant into the interlayer cavity, and the outlet end of the flow channel structure is provided with a water outlet structure for discharging coolant from the interlayer cavity.

[0007] An installation structure is provided on the flow channel structure for mounting blade assemblies;

[0008] The air intake connection structure is located at the inlet end of the flow channel structure and is used to connect to the outlet end of the fuel heater of the test vehicle platform.

[0009] An exhaust connection structure is located at the outlet end of the flow channel structure and is used to connect to an exhaust pipe.

[0010] As a further improvement to the above technical solution, the air intake connection structure includes an air intake flange disposed at the air intake end of the flow channel structure, and the water intake structure is disposed on the outer wall near the air intake flange.

[0011] As a further improvement to the above technical solution, the water inlet structure includes a water inlet on the outer wall at a preset incident angle, so that coolant is sprayed onto the air intake flange end face; two or more water inlets are evenly distributed circumferentially.

[0012] As a further improvement to the above technical solution, the exhaust connection structure includes an exhaust flange disposed at the outlet end of the flow channel structure, and the water outlet structure includes a plurality of drain holes evenly distributed along the circumference. The water outlet structure is connected to the exhaust pipe to allow the discharged coolant to mix with the high-temperature fuel gas discharged from the flow channel structure and be discharged through the exhaust pipe.

[0013] As a further improvement to the above technical solution, the flow area of ​​the water inlet structure is matched with the flow area of ​​the water outlet structure.

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

[0015] As a further improvement to the above technical solution, the flow channel structure is provided with a first mounting base and a second mounting base, which are used to install the total pressure probe and the total temperature probe, respectively.

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

[0017] As a further improvement to the above technical solution, the blade assembly includes a cooling blade and a blade mounting seat connected to the mounting structure, the blade mounting seat having a mounting structure that matches the shape of the cooling blade.

[0018] According to another aspect of the present invention, a test method is also provided, which includes the above-described high-temperature cooling effect test apparatus.

[0019] The present invention has the following beneficial effects:

[0020] The intake connection at the end of this test device connects to the outlet of the fuel heater on the test vehicle platform. The fuel heater provides high-temperature, high-pressure combustion gas, consistent with the actual operating conditions of the engine, into the inner channel of the flow channel structure. The structure of the inner channel is consistent with the actual shape and size of the engine's combustion gas flow passage, and the temperature and pressure of the introduced combustion gas are consistent with the actual operating conditions of the engine. By setting a double-wall structure to form a sandwich cavity and introducing coolant, the flow channel structure through which the high-temperature, high-pressure combustion gas is introduced is cooled down. The coolant flows in the sandwich cavity along the direction of combustion gas flow and is discharged from the water outlet at the outlet end, realizing the cooling and heat exchange of the flow channel structure. The temperature of the combustion gas in the flow channel exceeds 1200℃. Ordinary metal materials are difficult to work reliably and continuously at such high temperatures. However, based on the structure of this test device, the introduction of coolant through the sandwich cavity formed by the double-wall structure allows the test device to be made of ordinary stainless steel materials to realize the cooling effect test of turbine blades under high-temperature and high-pressure real environment, which saves costs to a large extent. At the same time, it can truly verify the cooling effect of turbine blades, improve the accuracy of turbine test verification results, and effectively calibrate and correct turbine cooling blade design.

[0021] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0022] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0023] Figure 1 This is a schematic diagram of a preferred embodiment of the present invention;

[0024] Figure 2 This is a cross-sectional view of the flow channel structure of a preferred embodiment of the present invention;

[0025] Figure 3 This is a schematic diagram of the probe mounting structure according to a preferred embodiment of the present invention.

[0026] Legend:

[0027] 1. Flow channel structure; 11. Inner wall; 2. Outer 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 blades; 21. Cooling air intake structure; 22. Blade mounting seat; 3. Air inlet connection structure; 4. Exhaust connection structure; 5. Water inlet connector; 6. First mounting seat; 7. Second mounting seat; 8. Total pressure probe; 9. Total temperature probe; 10. Graphite gasket. Detailed Implementation

[0028] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0029] Figure 1 This is a schematic diagram of a preferred embodiment of the present invention; Figure 2 This is a cross-sectional view of the flow channel structure of a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the probe mounting structure according to a preferred embodiment of the present invention.

[0030] like Figures 1 to 3 As shown, the high-temperature cooling effect test apparatus of this embodiment is used for testing the cooling effect of aero-engine turbine blades. The test apparatus includes:

[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 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. A water inlet structure 15 is provided at the inlet end of the flow channel structure 1 for introducing coolant into the interlayer cavity 14. A water outlet structure 16 is provided at the outlet end of the flow channel structure 1 for discharging coolant from the interlayer cavity 14.

[0032] Mounting structure 17 is provided on flow channel structure 1 and is used to mount blade assembly;

[0033] The air 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.

[0034] Exhaust connection structure 4 is located at the outlet end of flow channel structure 1 and is used to connect with exhaust pipe.

[0035] The blade assembly includes a cooling blade 2 to be tested. The cooling blade 2 is designed with a cooling air intake structure 21 and a cold air channel structure. Thermocouple measuring points are arranged on the surface of the cooling blade 2, and the surface temperature of the metal blade is measured by thermocouples to obtain the cooling efficiency characteristics of the blade surface. The blade assembly also includes a blade mounting seat 22 connected to the mounting structure 17. The blade mounting seat 22 has a mounting structure that matches the shape of the cooling blade 2. The mounting structure of the blade mounting seat 22 is designed to match different models and structures of cooling blades 2. The blade mounting seat 22 is fastened to the mounting structure 17 by bolts. The cooling blade 2 is inserted into the inner flow channel 13 of the mounting structure. The cooling air intake structure 21 (such as an air intake connector) at the root of the cooling blade 2 is connected to an external air source.

[0036] It is understandable that the air intake connection structure 3 at the end of this test device is connected to the outlet of the fuel heater on the test vehicle platform. The fuel heater provides high-temperature and high-pressure gas, consistent with the actual working conditions 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's gas flow channel, and the temperature and pressure of the gas are consistent with the actual operating conditions of the engine. By setting a double-wall structure to form a sandwich cavity 14 and introducing coolant, the flow channel structure 1 through which the high-temperature and high-pressure gas is introduced is cooled down. The coolant flows in the sandwich cavity 14 along the gas flow direction and exits from the outlet. The water outlet structure 16 at the end discharges water, achieving cooling and heat exchange for the flow channel structure 1. The gas temperature inside the flow channel exceeds 1200℃. Ordinary metal materials are difficult to work reliably and continuously at such high temperatures. However, based on the structure of this test device, coolant is introduced into the sandwich cavity 14 formed by the double-wall structure for heat exchange. The test device can be made of ordinary stainless steel materials to realize the cooling effect test of turbine blades under high temperature and high pressure in real environment, which saves costs to a large extent. At the same time, it can truly verify the cooling effect of turbine blades, improve the accuracy of turbine test verification results, and effectively calibrate and correct the design of turbine cooling blades 2.

[0037] Among them, the flow channel structure 1 shell is integrally formed by additive manufacturing, which avoids the difficulties of machining and welding of double shells, and at the same time has excellent high temperature resistance.

[0038] In this embodiment, the air inlet connection structure 3 includes an air inlet flange disposed at the air inlet end of the flow channel structure 1, and the water inlet structure 15 is disposed on the outer wall 12 near the air inlet flange, and a water inlet connector 5 is provided to connect to the water inlet pipeline, which does not affect the disassembly and connection of the bolts on the air inlet flange.

[0039] Furthermore, the water inlet structure 15 includes a water inlet on the outer wall 12 at a preset incident angle, so that the coolant is sprayed onto the end face of the air intake flange. By setting the water inlet on the outer wall 12 near the air intake flange and at a preset angle, the coolant can effectively cool the air intake flange while avoiding affecting the installation and removal of bolts on the air intake flange; two or more water inlets are evenly distributed circumferentially.

[0040] In this embodiment, the exhaust connection structure 4 includes an exhaust flange disposed at the outlet end of the flow channel structure 1, and the water outlet structure 16 is connected to the exhaust pipe. It is used to mix the discharged coolant with the high-temperature gas discharged from the flow channel structure 1 and discharge it through the exhaust pipe. The discharge coolant mixes with the high-temperature gas discharged from the flow channel structure 1, thereby cooling the discharged high-temperature gas. This allows the exhaust pipe to also be made of ordinary metal materials to achieve exhaust, greatly reducing the cost of the device. The water outlet structure 16 includes multiple drainage holes evenly distributed in a circumferential direction. Its structure is similar to the water outlet of a shower head, which greatly improves the mixing uniformity of the discharged cooling water and the high-temperature gas, maximizes the utilization of coolant efficiency, greatly improves the cooling effect, and reduces the gas temperature.

[0041] It should be understood that the flow area of ​​the water inlet structure 15 is matched with the flow area of ​​the water outlet structure 16, that is, the total area of ​​the water inlet holes is equal to the total area of ​​the water outlet holes, so as to avoid the liquid shortage in the interlayer cavity 14 and ensure the heat exchange effect.

[0042] In this embodiment, a turbulence support structure 18 is provided in the interlayer cavity 14. The turbulence support structure 18 is connected to the inner wall 11 and the outer wall 12 respectively. The turbulence support structure 18 includes multiple sets of reinforcing ribs, which are arranged along the length of the flow channel structure 1. Each set of reinforcing ribs includes multiple reinforcing ribs evenly distributed in the circumferential direction. The reinforcing ribs can support and connect the inner wall 11 and the outer wall 12, and at the same time turbulent the coolant to improve the heat exchange effect of the coolant. The shape of the reinforcing ribs can be designed as cylindrical, rhomboid, teardrop, or other different forms. Preferably, the reinforcing ribs with suitable shapes are designed based on simulation calculations.

[0043] In this embodiment, 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. 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, respectively. The total pressure probe 8, the total temperature probe 9 and the blade assembly are all detachable structures so that they can be replaced after damage and adapted to different models and specifications of cooling tests according to test requirements.

[0044] In this embodiment, 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. Graphite gaskets 10 are also provided at the mating parts of the blade assembly to achieve sealing and prevent gas leakage from the inner flow channel 13. The graphite gaskets 10 have good high temperature resistance and can adapt to the test environment.

[0045] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A high temperature cooling effect test device, used for the cooling effect test of aircraft engine turbine blades, characterized in that: The test equipment includes: The flow channel structure (1) has an inner flow channel (13) and is structured to match the gas flow channel of the engine; the flow channel structure (1) comprises 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); a water inlet structure (15) is provided at the inlet end of the flow channel structure (1) for introducing a coolant into the interlayer cavity (14); and a water outlet structure (16) is provided at the outlet end of the flow channel structure (1) for conducting the coolant out of the interlayer cavity (14); A mounting structure (17), arranged on the flow channel structure (1) and used for mounting a blade assembly; An air intake connection structure (3) is arranged at the inlet end of the flow channel structure (1) and is used to be connected to the outlet end of the fuel heater of the test vehicle bench; An exhaust connection structure (4) is arranged at the outlet end of the flow channel structure (1) and is used for connecting to an exhaust pipe.

2. The high temperature cooling efficiency test device according to claim 1, characterized in that: The air intake connection structure (3) comprises an air intake flange arranged at the air intake end of the flow channel structure (1), and the water intake structure (15) is arranged at a position on the outer wall (12) close to the air intake flange.

3. The high temperature cooling efficiency test device according to claim 2, characterized in that: The water inlet structure (15) comprises a water inlet opening at a preset incident angle on the outer wall (12) so that the coolant is sprayed onto the end face of the air inlet flange; two or more water inlets are evenly distributed along the circumference.

4. The high temperature cooling efficiency test device according to claim 1, characterized in that: 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) includes a plurality of drainage holes evenly arranged in a circumferential direction. The water outlet structure (16) is connected to the exhaust pipe and is used to mix the discharged coolant with the high-temperature combustion gas discharged from the flow channel structure (1) and discharge the mixture through the exhaust pipe.

5. The high temperature cooling efficiency test device according to any one of claims 1 to 4, characterized in that: The flow area of ​​the water inlet structure (15) matches the flow area of ​​the water outlet structure (16).

6. The high temperature cooling efficiency test device according to claim 1, characterized in that: A spoiler support structure (18) is arranged in the interlayer cavity (14), and the spoiler support structure (18) is respectively connected to the inner wall (11) and the outer wall (12).

7. The high temperature cooling efficiency test device according to claim 1, characterized in that: The flow channel structure (1) is provided with a first mounting seat (6) and a second mounting seat (7), which are used to mount a total pressure probe (8) and a total temperature probe (9), respectively.

8. The high temperature cooling efficiency test device according to claim 7, characterized in that: Graphite gaskets (10) are respectively 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).

9. The high temperature cooling efficiency test device according to claim 1, characterized in that: The blade assembly comprises a cooling blade (2) and a blade mounting seat (22) connected to the mounting structure (17); the blade mounting seat (22) has a mounting structure matching the shape of the cooling blade (2).

10. A test method, characterized in that: The high temperature cooling effect test device according to any one of claims 1 to 9 is used.

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