Turbine guide vane thermal deformation measuring device

Abstract

The invention relates to a turbine guide vane thermal deformation measuring device which comprises a base, a fan-shaped section turbine guide vane, a turbine guide vane thermal radial deformation measuring unit and a turbine guide vane thermal axial deformation measuring unit. The turbine guide vane thermal deformation measuring device can effectively simulate the thermal-force constraint state of the test turbine guide vane in the thermal state, and the thermal deformation measuring precision of the test turbine guide vane can be effectively improved by adopting the displacement transmission rod structure.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, in particular to a turbine guide vane thermal deformation measuring device. BACKGROUND

[0002] As a hot-end core stator component of aero-engine, turbine guide vane is subjected to extreme high temperature, high pressure, high-speed airflow scouring and complex stress for a long time. Generally, high-pressure turbine guide vane is directly exposed to high-temperature gas of 1100-1500℃, and bears huge thermal load, thus inevitably causing significant thermal deformation. The radial elongation of high-pressure turbine guide vane of a certain type of aero-engine can reach 0.8mm under maximum working condition.

[0003] Thermal deformation of turbine guide vane can cause deviation of blade profile from design value, affect the aerodynamic characteristics of gas flow passage, and increase flow loss. Meanwhile, turbine guide vane is connected with casing through rim plate structure, and sufficient thermal expansion space needs to be reserved for cold-state assembly. If thermal deformation is not accurately predicted, over-constraint or excessive clearance under hot-state assembly can be caused.

[0004] The deformation of turbine guide vane under hot-state working condition is relatively complex, mainly including radial and axial thermal expansion. Relatively, the temperature at the position of blade body is higher, and the temperature at the position of rim plate is lower, thus the overall thermal expansion of turbine guide vane is not uniform, which makes it difficult to measure the thermal deformation. In the existing turbine guide vane design process, the method of finite element analysis is often used to obtain the thermal deformation rule of turbine guide vane under engine working condition, or a thermal imager is used to monitor the temperature distribution on the surface of turbine guide vane, and the thermal deformation condition is indirectly inferred. Such analysis method is usually inaccurate, and is different from the actual thermal deformation rule of turbine guide vane.

[0005] Patent No. CN101315270B discloses a method for non-contact measurement of turbine blade deformation, i.e. by arranging proximity sensors around the periphery of turbine blade, respectively measuring the initial distance and the distance after deformation of the proximity sensors to the top end, upstream and downstream of turbine blade, and subtracting the two measurement values to obtain the radial displacement and axial displacement of turbine blade deformation. However, this method is mainly used for monitoring the creep deformation of turbine rotor blade under stress and high temperature, and the working temperature of proximity sensor used for measurement does not exceed 1000℃. The maximum temperature of turbine guide vane actually working in aero-engine under design state can reach 1500℃, and the ambient temperature is also far beyond the limit working temperature of proximity sensor (high-temperature-resistant type), thus this method cannot accurately measure the thermal deformation of turbine guide vane under real working condition of aero-engine. SUMMARY

[0006] In view of the deficiencies of the prior art, the present application aims to provide a turbine guide vane thermal deformation measuring device which can effectively simulate the thermal-mechanical constraint state of the test turbine guide vane under thermal state, and the displacement transmission rod structure can effectively improve the thermal deformation measuring precision of the test turbine guide vane.

[0007] The present application is realized by the following technical solutions.

[0008] A turbine guide vane thermal deformation measuring device comprises a base for supporting and positioning components, a fan-shaped turbine guide vane, a turbine guide vane thermal radial deformation measuring unit and a turbine guide vane thermal axial deformation measuring unit.

[0009] The fan-shaped turbine guide vane comprises a test turbine guide vane and auxiliary turbine guide vanes, and the fan-shaped turbine guide vane is fixed in an inner support frame by short pins, the inner support frame is fixed on the base, and the auxiliary turbine guide vanes are arranged on the circumferential two sides of the test turbine guide vane, respectively, each turbine guide vane is elastically locked by a connecting groove on the inner edge plate and outer edge plate structure and a spring sheet in the groove, and the edge plate structure and the blade body jointly constitute the internal boundary of the gas flow passage.

[0010] The turbine guide vane thermal radial deformation measuring unit comprises a radial displacement transmission rod support fixed on a support rod, a radial displacement transmission rod passing through the radial displacement transmission rod support, a radial displacement sensor support fixed on the support rod and a radial displacement sensor passing through the radial displacement sensor support, the support rod is fixed on the base, and the radial displacement transmission rod is connected with the radial displacement sensor and located on the same straight line.

[0011] The turbine guide vane thermal axial deformation measuring unit comprises an axial displacement transmission rod support fixed on a vertical support, an axial displacement transmission rod passing through the axial displacement transmission rod support, an axial displacement sensor support fixed on the vertical support and an axial displacement sensor passing through the axial displacement sensor support, the vertical support is fixed on the base, and the axial displacement transmission rod is connected with the axial displacement sensor and located on the same straight line.

[0012] Further, the installation angle θ of the fan-shaped turbine guide vane ranges from -60° to 60° with the normal direction of the top surface of the base as 0°.

[0013] In the turbine guide vane thermal deformation measuring device, the auxiliary turbine guide vanes are additionally arranged on the circumferential two sides of the test turbine guide vane, and the purpose is to accurately simulate the structural constraint of the test turbine guide vane under the actual installation state.

[0014] Further, the radial displacement transmission rod and the outer surface of the test turbine guide vane keep non-constrained contact in the radial direction, and the axial displacement transmission rod and the outer surface of the test turbine guide vane keep non-constrained contact in the axial direction.

[0015] Further, the ratio of the rod length L of the radial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1, and the ratio of the rod length L of the axial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1. r Further, the ratio of the rod length L of the radial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1, and the ratio of the rod length L of the axial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1. a Further, the ratio of the rod length L of the radial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1, and the ratio of the rod length L of the axial displacement transmission rod to the height H of the test turbine guide vane is not less than 3:1.

[0016] In the turbine guide vane thermal deformation measuring device, in view of the influence of high temperature, in order to avoid direct contact between the test turbine guide vane and the displacement sensor in each direction, a displacement transmission rod is arranged on the outer surface of the outer edge plate structure as a transition.

[0017] In the prior art, there are few research tests for turbine guide vane thermal deformation measurement, and the finite element analysis method is usually used to predict the thermal deformation rule, or the temperature distribution on the surface of the turbine guide vane is monitored to indirectly infer the thermal deformation. In the existing turbine blade deformation measurement method, the turbine rotor blade with relatively low working temperature is often used, and the turbine guide vane with higher working temperature is not applicable.

[0018] The turbine guide vane thermal deformation measuring device has the following advantages:

[0019] 1. The auxiliary turbine guide vanes are arranged on the circumferential two sides of the test turbine guide vane to accurately simulate the structural constraint of the test turbine guide vane in the actual installation state.

[0020] 2. In view of the influence of high temperature, in order to avoid direct contact between the test turbine guide vane and the displacement sensor in each direction and to affect the measurement accuracy of the thermal deformation, a displacement transmission rod is arranged on the outer surface of the outer edge plate as a transition. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 The figure is a structural schematic diagram of the application;

[0022] Figure 2 The figure is an installation range schematic diagram of the application;

[0023] Figure 3 The figure is a displacement transmission rod arrangement schematic diagram of the application;

[0024] In the figure: 100, base, 200, sector turbine guide vane, 3, turbine guide vane thermal radial deformation measurement unit, 4, turbine guide vane thermal axial deformation measurement unit;

[0025] 201 inner support frame, 2001 test turbine guide vane, 2002 auxiliary turbine guide vane;

[0026] 301 support rod, 302 radial displacement transmission rod support, 303 radial displacement sensor support, 304 radial displacement transmission rod, 305 radial displacement sensor;

[0027] 401 vertical support, 402 axial displacement transmission rod support, 403 axial displacement sensor support, 404 axial displacement transmission rod, 405 axial displacement sensor. DETAILED DESCRIPTION

[0028] The application will be further described below in connection with the drawings and specific embodiments, but not as a limitation of the application.

[0029] As Figure 1 and Figure 2As shown, the turbine guide vane thermal deformation measurement device of the present application comprises a base 100 for supporting and positioning various components, and a sector turbine guide vane 200, a turbine guide vane thermal radial deformation measurement unit 300 and a turbine guide vane thermal axial deformation measurement unit 400. The sector turbine guide vane 200 comprises a test turbine guide vane 2001 and an auxiliary turbine guide vane 2002, the sector turbine guide vane 200 is fixed in an inner support frame 201 by short pins, the inner support frame 201 is fixed on the base 100, the normal direction of the top surface of the base 100 is 0°, the installation angle θ of the sector turbine guide vane 200 ranges from -45° to 45°, and the auxiliary turbine guide vanes 2002 are arranged on the circumferential two sides of the test turbine guide vane 2001 to accurately simulate the structural constraints of the test turbine guide vane 2001 in the actual installation state, wherein each turbine guide vane is elastically locked by a connecting groove on the inner and outer edge plate structures and a spring sheet in the groove. The turbine guide vane thermal radial deformation measurement unit 300 comprises a radial displacement transmission rod support 302 fixed on a support rod 301, a radial displacement transmission rod 304 passing through the radial displacement transmission rod support 302, a radial displacement sensor support 303 fixed on the support rod 301, and a radial displacement sensor 305 passing through the radial displacement sensor support 303, and the support rod 301 is fixed on the base 100, wherein the radial displacement transmission rod 304 is connected with the radial displacement sensor 305 and located on the same straight line. The turbine guide vane thermal axial deformation measurement unit 400 comprises an axial displacement transmission rod support 402 fixed on a vertical support 401, an axial displacement transmission rod 404 passing through the axial displacement transmission rod support 402, an axial displacement sensor support 403 fixed on the vertical support 401, and an axial displacement sensor 405 passing through the axial displacement sensor support 403, and the vertical support 401 is fixed on the base 100, wherein the axial displacement transmission rod 404 is connected with the axial displacement sensor 405 and located on the same straight line.

[0030] As Figure 1 and Figure 3As shown, the fan-shaped segment turbine guide vane 200 blade surface is arranged with a hot flow pipeline (not marked in the figure) in the axial direction, high-temperature gas is passed into the hot flow pipeline to simulate the heat transfer process of the gas side of the turbine guide vane in the actual working process, the outer edge plate upper surface is arranged with a cold flow pipeline (not marked in the figure), and the cold flow pipeline is communicated with the inner cavity of each turbine guide vane, cooling gas is passed into the cold flow pipeline to simulate the heat transfer process of the cold gas side of the turbine guide vane in the actual working process. The test turbine guide vane 2001 is arranged with several thermocouples (not shown in the figure) on the outer surface by spot welding to monitor the temperature distribution, so as to ensure that the temperature of the blade surface is consistent with the temperature under the true working condition. The radial displacement transmission rod 304 keeps non-constrained contact with the outer surface of the test turbine guide vane 2001 in the radial direction, so as to measure the radial thermal deformation amount of the test turbine guide vane 2001 at different circumferential positions in real time, in addition, the ratio of the length L r of the radial displacement transmission rod 304 to the blade height H of the test turbine guide vane 2001 is equal to 5:1. The axial displacement transmission rod 404 keeps non-constrained contact with the outer surface of the test turbine guide vane 2001 in the axial direction, so as to measure the axial thermal deformation amount of the test turbine guide vane 2001 at different circumferential positions in real time, in addition, the ratio of the length L a of the axial displacement transmission rod 404 to the blade height H of the test turbine guide vane 2001 is equal to 5:1.

[0031] The above only describes the preferred embodiments of the present application and cannot be understood as a limitation on the patent scope of the application. It should be noted that for ordinary skilled persons in the art, some modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the patent protection scope of the present application should be subject to the appended claims.

Claims

1. A turbine guide vane hot deformation measurement device, characterized by, The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line.

2. The turbine guide vane hot deformation measurement device of claim 1, wherein, The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line. The turbine guide vane hot radial deformation measuring unit (300) comprises a radial displacement transmission rod support (302) fixed on a support rod (301), a radial displacement transmission rod (304) penetrating through the radial displacement transmission rod support (302), a radial displacement sensor support (303) fixed on the support rod (301) and a radial displacement sensor (305) penetrating through the radial displacement sensor support (303), wherein the support rod (301) is fixed on the base (100), and the radial displacement transmission rod (304) is connected with the radial displacement sensor (305) and located on the same straight line.

3. The turbine guide vane hot deformation measurement device of claim 1, wherein, The radial displacement transmission rod (304) keeps non-constrained contact with the outer surface of the test turbine guide vane (2001) in the radial direction, the rod length L of the radial displacement transmission rod (304) r The ratio of the rod length L of the axial displacement transmission rod (404) to the height H of the test turbine guide vane (2001) is not less than 3:

1. The axial displacement transmission rod (404) keeps non-constrained contact with the outer surface of the test turbine guide vane (2001) in the axial direction, the rod length L of the axial displacement transmission rod (404) a The ratio of the rod length L of the axial displacement transmission rod (404) to the height H of the test turbine guide vane (2001) is not less than 3:1.

Images