A twin-rotor turbine performance test piece

Abstract

This application provides a dual-rotor turbine performance test specimen, comprising: an inlet casing assembly, a high-pressure turbine guide vane assembly, a high-pressure turbine rotor assembly, a low-pressure turbine guide vane assembly, a low-pressure turbine rotor assembly, and an exhaust casing assembly. The high-pressure turbine rotor assembly and the low-pressure turbine rotor assembly are driven independently, thereby forming the dual-rotor turbine performance test specimen. The dual-rotor turbine test specimen provided by this application enables simultaneous performance testing of high- and low-pressure turbines in aero-engines. Through testing, the matching relationship between the high- and low-pressure turbines can be explored, their performance can be obtained, and the design capabilities for matching high- and low-pressure turbines can be improved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine testing, and specifically relates to a dual-rotor turbine performance test piece. Background Technology

[0002] High- and low-pressure turbine matching design is one of the challenges in aero-engine design, and experimental research is an important means to obtain high- and low-pressure turbine matching performance. By conducting high- and low-pressure turbine performance tests, exploring the matching relationship between high- and low-pressure turbines, and obtaining high- and low-pressure turbine performance data, it is of great significance for improving the design capabilities of high- and low-pressure turbine matching.

[0003] like Figure 1 The diagram shows the structure of a conventional turbine performance test piece with a single rotor. It is driven by a turbine 102 connected to a rotor system 101, but it can only perform performance tests on the high-pressure turbine or the low-pressure turbine separately to obtain test performance measurement results.

[0004] However, as a low-pressure turbine, it is difficult to accurately simulate the flow field conditions at the inlet of the low-pressure turbine (outlet of the high-pressure turbine) when testing it on a single-rotor turbine performance tester. In the performance test of the low-pressure turbine, the circumferential average result of the flow calculation given by the high-pressure turbine design can be used to complete the performance test of the low-pressure turbine stage and obtain the characteristics of the low-pressure turbine. This method of replacing experiment with calculation inevitably causes certain calculation errors and cannot be verified, thus affecting the design matching relationship between the high-pressure and low-pressure turbines. Summary of the Invention

[0005] The purpose of this application is to provide a dual-rotor turbine performance test piece to solve or mitigate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a dual-rotor turbine performance test piece, comprising: an intake casing assembly, a high-pressure turbine guide assembly, a high-pressure turbine rotor assembly, a low-pressure turbine guide assembly, a low-pressure turbine rotor assembly, and an exhaust casing assembly, wherein the high-pressure turbine rotor assembly and the low-pressure turbine rotor assembly are driven independently, thereby forming a dual-rotor turbine performance test piece.

[0007] Furthermore, the intake casing assembly includes an intake load-bearing casing, an intake measurement casing, an intake casing bleed pipe, a high-pressure oil inlet pipe, a high-pressure connecting oil pipe, a high-pressure turbine first support bearing housing, a high-pressure turbine first support sealing ring, a high-pressure turbine second support bearing housing, and a high-pressure turbine second support sealing ring.

[0008] The intake bearing housing is fixedly connected to the intake measuring housing. The intake housing air intake pipe is installed on the intake bearing housing and extends into the interior of the intake bearing housing. It is used to introduce sealing gas to balance the axial force of the high-pressure turbine rotor and the sealing of the bearing cavity. The high-pressure oil inlet pipe and the high-pressure connecting oil pipe are fixedly installed on the intake bearing housing. They are used to introduce lubricating oil into the support bearing of the high-pressure turbine rotor assembly for lubrication and cooling.

[0009] The first and second support bearing housings of the high-pressure turbine are mounted on the intake bearing casing to support the support bearings. The first and second support sealing rings of the high-pressure turbine are mounted on the intake bearing casing to form sealing cavities for the two high-pressure turbine support points.

[0010] Furthermore, the high-pressure turbine guide vane assembly includes a high-pressure turbine guide vane sprue and a high-pressure turbine guide vane. The high-pressure turbine guide vane sprue is connected to the high-pressure turbine guide vane and is used to introduce simulated cooling gas to simulate the cooling of the high-pressure turbine guide vanes and high-pressure turbine rotor blades.

[0011] Furthermore, the high-pressure turbine rotor assembly includes a high-pressure turbine rotor, a high-pressure turbine shaft, a high-pressure turbine first pivot bearing, a high-pressure turbine second pivot bearing, and a high-pressure gear coupling.

[0012] The high-pressure turbine rotor is connected to the high-pressure turbine shaft. The high-pressure turbine shaft is supported on the high-pressure turbine first support bearing and the high-pressure turbine second support bearing via the high-pressure turbine first support bearing and the high-pressure turbine second support bearing. The high-pressure turbine shaft is connected to the high-pressure gear coupling. The other end of the high-pressure gear coupling is connected to the dynamometer adapter shaft of the tester for power measurement of the high-pressure turbine rotor.

[0013] Furthermore, the low-pressure turbine guide vane assembly includes a low-pressure turbine guide vane sprue and a low-pressure turbine guide vane. The low-pressure turbine guide vane sprue is connected to the low-pressure turbine guide vane and is used to introduce simulated cooling gas to simulate the cooling of the low-pressure turbine guide vanes and the high-pressure turbine rotor blades.

[0014] Furthermore, the low-pressure turbine rotor assembly includes a low-pressure turbine rotor, a low-pressure turbine shaft, a low-pressure turbine first pivot bearing, a low-pressure turbine second pivot bearing, and a low-pressure gear coupling.

[0015] The low-pressure turbine rotor is connected to the low-pressure turbine shaft, which is supported on the low-pressure turbine first support bearing and the low-pressure turbine second support bearing via the low-pressure turbine first support bearing and the low-pressure turbine second support bearing. The low-pressure turbine shaft is connected to the low-pressure gear coupling, and the other end of the low-pressure gear coupling is connected to the dynamometer adapter shaft of the tester for power measurement of the low-pressure turbine rotor.

[0016] Furthermore, the exhaust casing assembly includes an exhaust load-bearing casing, an exhaust measurement casing, an exhaust casing bleed pipe, a low-pressure oil inlet pipe, a low-pressure connecting oil pipe, a low-pressure turbine first support bearing housing, a low-pressure turbine first support sealing ring, a low-pressure turbine second support bearing housing, and a low-pressure turbine second support sealing ring.

[0017] The exhaust load bearing housing is fixedly connected to the exhaust measurement housing. The exhaust housing air intake pipe is installed on the exhaust load bearing housing and extends into the interior of the exhaust load bearing housing. It is used to introduce sealing gas to balance the axial force of the low-pressure turbine rotor and the sealing of the bearing cavity. The low-pressure oil inlet pipe and the low-pressure connecting oil pipe are installed on the exhaust load bearing housing. They are used to introduce lubricating oil into the support bearing of the low-pressure turbine rotor assembly for lubrication and cooling.

[0018] The first and second support bearing seats of the low-pressure turbine are installed on the exhaust load-bearing casing; the first and second support sealing rings of the low-pressure turbine are installed on the exhaust load-bearing casing to form sealing cavities for the two low-pressure turbine support points.

[0019] Furthermore, the first pivot bearing of the high-pressure turbine and the first pivot bearing of the low-pressure turbine are ball bearings, while the second pivot bearing of the high-pressure turbine and the second pivot bearing of the low-pressure turbine are roller bearings. The dual-rotor turbine test piece provided in this application enables simultaneous performance testing of the high- and low-pressure turbines of aero-engines. Through testing, the matching relationship between the high- and low-pressure turbines can be explored, the performance of the high- and low-pressure turbines can be obtained, and the matching design capability of the high- and low-pressure turbines can be improved. Attached Figure Description

[0020] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0021] Figure 1 This is a schematic diagram of the structure of a conventional turbine performance test piece with a single rotor structure in the prior art.

[0022] Figure 2 This is a schematic diagram of the unit body of the dual-rotor turbine performance test piece of this application.

[0023] Figure 3 This is a schematic diagram of the components of the dual-rotor turbine performance test piece of this application.

[0024] Figure label:

[0025] 210-Intake Casing Assembly

[0026] 211-Intake Support Casing

[0027] 212-Intake Measurement Casing

[0028] 213-Intake casing bleed pipe

[0029] 214-High Pressure Oil Inlet Pipe

[0030] 215-High Pressure Connecting Oil Pipe

[0031] 216-High Pressure Turbine First Support Bearing Housing

[0032] 217-High Pressure Turbine First Support Point Sealing Ring

[0033] 218-Second Support Bearing Housing of High Pressure Turbine

[0034] 219-Second Support Point Sealing Ring of High Pressure Turbine

[0035] 220-High Pressure Turbine Guide Components

[0036] 221-High Pressure Turbine Guide Air Pipe

[0037] 222-High Pressure Turbine Guide

[0038] 230-High Pressure Turbine Rotor Assembly

[0039] 231-High Pressure Turbine Rotor

[0040] 232-High Pressure Turbine Shaft

[0041] 233-High Pressure Turbine First Support Bearing

[0042] 234 - High-pressure turbine second pivot bearing

[0043] 235-High Pressure Gear Coupling

[0044] 240-Low-pressure turbine guide assembly

[0045] 241-Low-pressure turbine guide vane bleed pipe

[0046] 242-Low-pressure turbine guide

[0047] 250-Low-Pressure Turbine Rotor Assembly

[0048] 251-Low-pressure turbine rotor

[0049] 252-Low-pressure turbine shaft

[0050] 253-Low-pressure turbine first pivot bearing

[0051] 254 - Low-pressure turbine second pivot bearing

[0052] 255-Low-pressure gear coupling

[0053] 260-Exhaust Casing Assembly

[0054] 261-Exhaust bearing casing

[0055] 262-Exhaust Measurement Casing

[0056] 263-Exhaust casing bleed pipe

[0057] 264-Low-pressure oil inlet pipe

[0058] 265-Low-pressure oil pipe

[0059] 266-Low-pressure turbine first pivot bearing housing

[0060] 267-Low-pressure turbine first pivot sealing ring

[0061] 268-Low-pressure turbine second pivot bearing housing

[0062] 269-Low-pressure turbine second pivot sealing ring Detailed Implementation

[0063] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0064] This application provides a dual-rotor turbine performance test specimen structure. By conducting dual-rotor turbine test specimens, the working matching of high-pressure and low-pressure turbines is studied and verified, the performance parameters of high-pressure and low-pressure turbine matching are obtained, and the high-pressure and low-pressure turbines are designed and adjusted to ensure that the high-pressure and low-pressure turbines work in an optimal state, thus ensuring the performance level of the turbine components in the whole machine.

[0065] like Figure 2 and Figure 3 As shown, the dual-rotor turbine performance test piece provided in this application includes six unit bodies, namely: intake casing assembly 210, high-pressure turbine guide assembly 220, high-pressure turbine rotor assembly 230, low-pressure turbine guide assembly 240, low-pressure turbine rotor assembly 250 and exhaust casing assembly 260.

[0066] The intake casing assembly 210 includes an intake load-bearing casing 211, an intake measuring casing 212, an intake casing bleed pipe 213, a high-pressure oil inlet pipe 214, a high-pressure connecting oil pipe 215, a high-pressure turbine first support bearing housing 216, a high-pressure turbine first support sealing ring 217, a high-pressure turbine second support bearing housing 218, and a high-pressure turbine second support sealing ring 219. The intake load-bearing casing 211 is fixedly connected to the intake measuring casing 212. The intake casing bleed pipe 213 is installed on the intake load-bearing casing 211 and extends into its interior. The high-pressure oil inlet pipe 214 and the high-pressure connecting oil pipe 215 are fixedly installed on the intake load-bearing casing 211. The high-pressure turbine first support bearing housing 216 and the high-pressure turbine second support bearing housing 218 are installed on the intake load-bearing casing 211 to support the support bearings. The high-pressure turbine first support sealing ring 217 and the high-pressure turbine second support sealing ring 219 are installed on the intake bearing casing 211 of the intake casing assembly 210 to form sealing cavities for the two high-pressure turbine supports.

[0067] The high-pressure turbine guide assembly 220 includes a high-pressure turbine guide sprue 221 and a high-pressure turbine guide 222, which are installed on the rear side of the intake casing assembly 210. The high-pressure turbine guide sprue 221 is connected to the high-pressure turbine guide 222.

[0068] The high-pressure turbine rotor assembly 230 includes a high-pressure turbine rotor 231, a high-pressure turbine shaft 232, a high-pressure turbine first support bearing 233, a high-pressure turbine second support bearing 234, and a high-pressure gear coupling 235. The high-pressure turbine rotor 231 is connected to the high-pressure turbine shaft 232, which is supported on the high-pressure turbine first support bearing seat 216 and the high-pressure turbine second support bearing seat 218 via the high-pressure turbine first support bearing 233 and the high-pressure turbine second support bearing 234. The high-pressure turbine shaft 232 is connected to and driven by the high-pressure gear coupling 235.

[0069] The low-pressure turbine guide assembly 240 includes a low-pressure turbine guide sprue 241 and a low-pressure turbine guide 242, which are installed on the rear side of the high-pressure turbine rotor assembly 230. The low-pressure turbine guide sprue 241 is connected to the low-pressure turbine guide 242.

[0070] The low-pressure turbine rotor assembly 250 includes a low-pressure turbine rotor 251, a low-pressure turbine shaft 252, a low-pressure turbine first pivot bearing 253, a low-pressure turbine second pivot bearing 254, and a low-pressure gear coupling 255. The low-pressure turbine rotor 251 is connected to the low-pressure turbine shaft 252, which is supported on a low-pressure turbine first pivot bearing seat 266 and a low-pressure turbine second pivot bearing seat 268 via the low-pressure turbine first pivot bearing 253 and the low-pressure turbine second pivot bearing 254. The low-pressure turbine shaft 252 is connected to and driven by the low-pressure gear coupling 255.

[0071] The exhaust casing assembly 260 includes an exhaust load-bearing casing 261, an exhaust measurement casing 262, an exhaust casing bleed pipe 263, a low-pressure oil inlet pipe 264, a low-pressure connecting oil pipe 265, a low-pressure turbine first support bearing housing 266, a low-pressure turbine first support sealing ring 267, a low-pressure turbine second support bearing housing 268, and a low-pressure turbine second support sealing ring 269. The exhaust load-bearing casing 261 is fixedly connected to the exhaust measurement casing 262. The exhaust casing bleed pipe 263 is installed on the exhaust load-bearing casing 261 and extends into its interior. The low-pressure oil inlet pipe 264 and the low-pressure connecting oil pipe 265 are installed on the exhaust load-bearing casing 261. The low-pressure turbine first support bearing housing 266 and the low-pressure turbine second support bearing housing 268 are installed on the exhaust load-bearing casing 261. The low-pressure turbine first support sealing ring 267 and the low-pressure turbine second support sealing ring 269 are installed on the exhaust load-bearing casing 261 of the exhaust casing assembly 260 to form sealing cavities for the two low-pressure turbine supports.

[0072] In the dual-rotor turbine performance test specimen of this application, the high-pressure turbine rotor assembly 230 and the low-pressure turbine rotor assembly 250 adopt independent support schemes to avoid vibration coupling problems. Specifically, the test specimen has four pivot bearings for rotor support: the first pivot bearing 233 and the second pivot bearing 234 of the high-pressure turbine support the high-pressure turbine rotor 231; the first pivot bearing 253 and the second pivot bearing 254 of the low-pressure turbine support the low-pressure turbine rotor 251. The first pivot bearings 233 and 253 of the high-pressure turbine are ball bearings, while the second pivot bearings 234 and 254 of the high-pressure turbine are roller bearings.

[0073] The dual-rotor turbine performance test specimen of this application provides a reliable force transmission scheme, ensuring stable and reliable operation of the test specimen. The axial and radial forces borne by the high-pressure turbine rotor 231 are transmitted to the high-pressure turbine first support bearing 233 and the high-pressure turbine second support bearing 234, then to the high-pressure turbine first support bearing housing 216 and the high-pressure turbine second support bearing housing 218, and finally to the inlet bearing housing 211. The inlet bearing housing 211 and the test chamber inlet volute (grounded) transfer the load of the high-pressure turbine rotor 231 to the test chamber. The force transmission path of the low-pressure turbine rotor 251 is similar to that of the high-pressure turbine rotor 231. The axial and radial forces borne by the low-pressure turbine rotor 251 are transmitted to the first support bearing 253 and the second support bearing 254 of the low-pressure turbine, then to the first support bearing housing 266 and the second support bearing housing 268 of the low-pressure turbine, and finally to the exhaust load-bearing casing 261. The exhaust load-bearing casing 261 and the exhaust volute (grounded) of the test apparatus transfer the load of the low-pressure turbine rotor to the test apparatus.

[0074] The dual-rotor turbine performance test specimen provided in this application employs a front-to-back power output method for the high / low-pressure turbine rotor assembly, ensuring accurate and reliable power measurement of the test specimen. Specifically, one end of the high-pressure gear coupling 235 is connected to the high-pressure turbine shaft 232, and the other end is connected to the dynamometer adapter shaft of the test apparatus, used for power measurement of the high-pressure turbine rotor 231. The power output method of the low-pressure turbine rotor is similar to that of the high-pressure rotor; one end of the low-pressure gear coupling 255 is connected to the low-pressure turbine shaft 252, and the other end is connected to the dynamometer adapter shaft of the test apparatus, used for power measurement of the low-pressure turbine rotor 251.

[0075] The dual-rotor turbine performance test specimen of this application has a rationally designed bleed and exhaust structure to ensure reliable cooling and sealing of the test specimen. Simulated cooling gas and sealing gas are introduced through the high-pressure turbine guide vane bleed pipe 221 and the inlet casing bleed pipe 213, respectively, to simulate the cooling of the high-pressure turbine guide vanes and high-pressure turbine rotor blades, and also to balance the axial force of the high-pressure turbine rotor. Simultaneously, sealing gas is introduced into the sealing cavities at the first support sealing ring 217 and the second support sealing ring 219 of the high-pressure turbine to seal the lubricating oil cavities at the first and second support points of the high-pressure turbine. Simulated cooling gas and sealing gas are introduced through the low-pressure turbine guide vane bleed pipe 241 and the exhaust casing bleed pipe 263, respectively, to simulate the cooling of the low-pressure turbine guide vanes and low-pressure turbine rotor blades, and also to balance the axial force of the low-pressure turbine rotor. Simultaneously, sealing gas is introduced into the sealing chambers at the sealing rings 267 and 269 of the first support point of the low-pressure turbine to achieve sealing of the lubricating oil chambers at the first and second support points of the low-pressure turbine.

[0076] The dual-rotor turbine performance test specimen of this application has a rationally designed lubrication system structure, ensuring reliable cooling and lubrication of the test specimen. Lubricating oil is introduced into the support bearings of the high-pressure turbine rotor 231 through the high-pressure oil inlet pipe 214 and the high-pressure connecting oil pipe 215, achieving lubrication and cooling of the first support bearing 233 and the second support bearing 234 of the high-pressure turbine. Lubricating oil is introduced into the support bearings of the low-pressure turbine rotor 251 through the low-pressure oil inlet pipe 264 and the low-pressure connecting oil pipe 265, achieving lubrication and cooling of the first support bearing 253 and the second support bearing 254 of the low-pressure turbine.

[0077] The dual-rotor turbine performance test specimen of this application has a rationally designed measurement structure, which can accurately obtain the test process parameters. The test specimen is equipped with an inlet measuring casing 212 and an exhaust measuring casing 262 for measuring the performance parameters of the high-pressure turbine inlet and the low-pressure turbine outlet. The performance parameters of the low-pressure turbine inlet (high-pressure turbine outlet) can be obtained by modifying the low-pressure turbine guide vanes for testing.

[0078] The dual-rotor turbine test specimen provided in this application enables simultaneous performance testing of high- and low-pressure turbines in aero-engines. Through these tests, the matching relationship between the high- and low-pressure turbines can be explored, their performance can be obtained, and the design capabilities for matching high- and low-pressure turbines can be improved.

[0079] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A dual-rotor turbine performance test specimen, characterized in that, include: The test specimen comprises an intake casing assembly, a high-pressure turbine guide assembly, a high-pressure turbine rotor assembly, a low-pressure turbine guide assembly, a low-pressure turbine rotor assembly, and an exhaust casing assembly. The high-pressure turbine rotor assembly and the low-pressure turbine rotor assembly are driven independently, thus forming a dual-rotor turbine performance test piece. The intake casing assembly includes an intake load-bearing casing, an intake measurement casing, an intake casing bleed pipe, a high-pressure oil inlet pipe, a high-pressure connecting oil pipe, a high-pressure turbine first support bearing housing, a high-pressure turbine first support sealing ring, a high-pressure turbine second support bearing housing, and a high-pressure turbine second support sealing ring. The intake bearing housing is fixedly connected to the intake measuring housing. The intake housing air intake pipe is installed on the intake bearing housing and extends into the interior of the intake bearing housing. It is used to introduce sealing gas to balance the axial force of the high-pressure turbine rotor and the sealing of the bearing cavity. The high-pressure oil inlet pipe and the high-pressure connecting oil pipe are fixedly installed on the intake bearing housing. They are used to introduce lubricating oil into the support bearing of the high-pressure turbine rotor assembly for lubrication and cooling. The first and second support bearing housings of the high-pressure turbine are mounted on the intake bearing casing to support the support bearings. The first and second support sealing rings of the high-pressure turbine are mounted on the intake bearing casing to form sealing cavities for the two high-pressure turbine support points.

2. The dual-rotor turbine performance test specimen as described in claim 1, characterized in that, The high-pressure turbine guide vane assembly includes a high-pressure turbine guide vane sprue and a high-pressure turbine guide vane. The high-pressure turbine guide vane sprue is connected to the high-pressure turbine guide vane and is used to introduce simulated cooling gas to simulate the cooling of the high-pressure turbine guide vanes and high-pressure turbine rotor blades.

3. The dual-rotor turbine performance test specimen as described in claim 2, characterized in that, The high-pressure turbine rotor assembly includes a high-pressure turbine rotor, a high-pressure turbine shaft, a high-pressure turbine first support bearing, a high-pressure turbine second support bearing, and a high-pressure gear coupling. The high-pressure turbine rotor is connected to the high-pressure turbine shaft. The high-pressure turbine shaft is supported on the high-pressure turbine first support bearing and the high-pressure turbine second support bearing via the high-pressure turbine first support bearing and the high-pressure turbine second support bearing. The high-pressure turbine shaft is connected to the high-pressure gear coupling. The other end of the high-pressure gear coupling is connected to the dynamometer adapter shaft of the tester for power measurement of the high-pressure turbine rotor.

4. The dual-rotor turbine performance test specimen as described in claim 3, characterized in that, The low-pressure turbine guide vane assembly includes a low-pressure turbine guide vane sprue and a low-pressure turbine guide vane. The low-pressure turbine guide vane sprue is connected to the low-pressure turbine guide vane and is used to introduce simulated cooling gas to simulate the cooling of the low-pressure turbine guide vanes and the high-pressure turbine rotor blades.

5. The dual-rotor turbine performance test specimen as described in claim 4, characterized in that, The low-pressure turbine rotor assembly includes a low-pressure turbine rotor, a low-pressure turbine shaft, a low-pressure turbine first pivot bearing, a low-pressure turbine second pivot bearing, and a low-pressure gear coupling. The low-pressure turbine rotor is connected to the low-pressure turbine shaft, which is supported on the low-pressure turbine first support bearing and the low-pressure turbine second support bearing via the low-pressure turbine first support bearing and the low-pressure turbine second support bearing. The low-pressure turbine shaft is connected to the low-pressure gear coupling, and the other end of the low-pressure gear coupling is connected to the dynamometer adapter shaft of the tester for power measurement of the low-pressure turbine rotor.

6. The dual-rotor turbine performance test specimen as described in claim 5, characterized in that, The exhaust casing assembly includes an exhaust load-bearing casing, an exhaust measurement casing, an exhaust casing sump pipe, a low-pressure oil inlet pipe, a low-pressure connecting oil pipe, a low-pressure turbine first support bearing housing, a low-pressure turbine first support sealing ring, a low-pressure turbine second support bearing housing, and a low-pressure turbine second support sealing ring. The exhaust load bearing housing is fixedly connected to the exhaust measurement housing. The exhaust housing air intake pipe is installed on the exhaust load bearing housing and extends into the interior of the exhaust load bearing housing. It is used to introduce sealing gas to balance the axial force of the low-pressure turbine rotor and the sealing of the bearing cavity. The low-pressure oil inlet pipe and the low-pressure connecting oil pipe are installed on the exhaust load bearing housing. They are used to introduce lubricating oil into the support bearing of the low-pressure turbine rotor assembly for lubrication and cooling. The first and second support bearing seats of the low-pressure turbine are installed on the exhaust load-bearing casing; the first and second support sealing rings of the low-pressure turbine are installed on the exhaust load-bearing casing to form sealing cavities for the two low-pressure turbine support points.

7. The dual-rotor turbine performance test specimen as described in claim 6, characterized in that, The first support bearing of the high-pressure turbine and the first support bearing of the low-pressure turbine are ball bearings, and the second support bearing of the high-pressure turbine and the second support bearing of the low-pressure turbine are roller bearings.

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