A high-speed counter-rotating turbine rotating disc cavity flow heat exchange test structure

Abstract

The application provides a high-rotating-speed counter-rotating turbine rotating disc cavity flow heat exchange test structure, and belongs to the technical field of aero-engine tests.The test structure comprises a rotor structure and a stator structure.The rotor structure comprises a left rotor assembly and a right rotor assembly which are independently arranged and symmetrically arranged left and right.The stator structure comprises a left bearing seat assembly, a right bearing seat assembly and a test piece engine case assembly.The left bearing seat assembly supports the left rotor assembly, and the right bearing seat assembly supports the right rotor assembly, so as to realize the lubrication of the bearings in the rotor assembly.The test piece engine case assembly is connected with the left bearing seat assembly and the right bearing seat assembly, is used for providing a flowing air flow into the disc cavity, and realizes the simulation of the working environment of the turbine disc.The test structure provided by the application can simulate the actual situation of the real turbine structure and the real working state of the aero-engine, and can also simulate the actual working state of the counter-rotating turbine disc.

Description

Technical Field

[0001] This application belongs to the field of aero-engine testing, and specifically relates to a high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure. Background Technology

[0002] like Figure 1 The diagram shows an existing rotating disk cavity flow heat transfer test structure 100, which includes a front shaft 101, a front bearing 102, a rear shaft 103, a rear bearing 104, a front casing 105, a rear casing 106, a middle casing 107, and a casing support ring 108. The front shaft 101 is supported on the front bearing 102, and the rear shaft 103 is supported on the rear bearing 104. The front casing 105 and the rear casing 106 are respectively sealed to the front shaft 101 and the rear shaft 103 through grates. The middle casing 107 connects the front casing 105 and the rear casing 106. The casing support ring 108 connects the middle casing 107 and the front casing 105 to improve its rigidity.

[0003] Because the front bearing 102 and rear bearing 104 are both independent of the stator casing formed by the front casing 105, rear casing 106, middle casing 107, and casing support ring 108, the concentricity of the rotor and stator cannot be guaranteed, resulting in a low test speed and an inability to simulate the actual turbine structure and working conditions of an aero-engine. In this test configuration, the front shaft 101 and rear shaft 103 are driven by a single transmission input, which fails to simulate the actual working conditions of the counter-rotating turbine disk.

[0004] Therefore, a test structure is needed that can simulate the actual turbine structure and working conditions of an aero-engine at high speeds, and that can enable two rotating parts to rotate at different speeds to simulate the actual working conditions of the engine's counter-rotating turbine disk. Summary of the Invention

[0005] The purpose of this application is to provide a high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure to solve or alleviate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure, including: a rotor structure and a stator structure, wherein the rotor structure includes a left rotor assembly and a right rotor assembly that are independent of each other, and the left rotor assembly and the right rotor assembly are symmetrically arranged left and right;

[0007] The stator structure includes a left bearing housing assembly, a right bearing housing assembly, and a test specimen casing assembly. The left bearing housing assembly supports the left rotor assembly, and the right bearing housing assembly supports the right rotor assembly to achieve lubrication of the bearings within the rotor assembly. The test specimen casing assembly connects the left bearing housing assembly and the right bearing housing assembly to provide airflow into the disk cavity, thereby simulating the working environment of the turbine disk.

[0008] Furthermore, both the left rotor assembly and the right rotor assembly include a rotating shaft, a front sealing ring, an oil baffle ring, an outer bearing, an inner bearing, a transition journal, and a lock nut;

[0009] The front sealing ring, oil baffle ring, and transition journal are installed on the rotating shaft. The front sealing ring and oil baffle ring are used to restrict the outer bearing installed on the rotating shaft. The inner bearing is installed on the transition journal. The front sealing ring and transition journal are sealed with the left bearing housing assembly or the right bearing assembly through a sealing structure.

[0010] The rotating shaft and the adapter journal are connected by a spline. The front end of the adapter journal is connected to the rotating shaft by an inter-shaft boss to ensure coaxiality, and the rear end of the adapter journal is fastened by a lock nut.

[0011] Furthermore, the adapter journal is fitted with flange edges according to different sizes of turbine disks to meet the needs of different tests.

[0012] Furthermore, the outer bearing is a double-direction angular contact ball bearing, and the inner bearing is a cylindrical roller bearing.

[0013] Furthermore, the left rotor assembly and the right rotor assembly also include a cover plate or a lead wire conduit. The cover plate is installed on the inner end of the shaft to maintain the pressure inside the test piece and to ensure that the high-temperature gas inside the cavity does not leak. The lead wire conduit is used to lead out the test lead wire on the test turbine disk.

[0014] Furthermore, both the left bearing housing assembly and the right bearing housing assembly include a bearing housing, a sealing housing, a bearing housing sealing ring and an inter-shaft sealing ring, an outer bearing oil supply ring, an inner bearing oil supply ring, and a base.

[0015] The bearing housing is used to support the outer bearing and the inner bearing. The bearing housing is integrally machined to ensure the coaxiality of the outer bearing and the inner bearing.

[0016] The outer bearing oil supply ring and the inner bearing oil supply ring are mounted on the bearing housing and face the outer bearing and the inner bearing respectively, and are used to provide lubricating oil to the bearing;

[0017] The sealing housing is installed at one end of the bearing housing to form a sealing structure with the front sealing ring of the shaft. The inter-shaft sealing ring and the outer bearing oil supply ring are installed at the other end of the bearing housing to form a sealing structure with the transition journal.

[0018] The bearing housing and sealing casing are both equipped with air vents to provide sealing air and ensure that the lubricating oil does not leak.

[0019] The base is cast to provide support for the bearing housing while enhancing the rigidity of the fulcrum and suppressing vibrations during testing.

[0020] Furthermore, the test specimen casing assembly includes a front casing, an inner casing support ring, a middle casing, and a rear casing. The front casing is connected to the bearing housing in the left bearing housing assembly, and the rear casing is connected to the bearing housing in the right bearing housing assembly. The front casing, the inner casing support ring, the middle casing, and the rear casing are connected by connectors.

[0021] The front casing, rear casing, and middle casing are equipped with air intake pipes, through which air is supplied to the turbine disk cavity of the test piece to simulate the working environment of the turbine disk.

[0022] Furthermore, the bearing housing in the left bearing housing assembly is connected to the front casing via a connector, and the bearing housing in the right bearing housing assembly is connected to the rear casing via an axial floating connection.

[0023] Furthermore, the axial floating connection between the bearing housing and the rear casing in the right bearing housing assembly is as follows: the rear bearing housing and the rear casing are positioned by a flat key and there is a fitting gap between the rear bearing housing and the rear casing. A sealing ring is set in the fitting gap, thereby forming an axial floating connection structure.

[0024] Figure label:

[0025] 100-Rotating disk cavity flow heat transfer test structure

[0026] 101-Front Axle

[0027] 102-Front Bearing

[0028] 103-Rear Axle

[0029] 104-Rear Bearing

[0030] 105-Front Casing

[0031] 106-Rear Casing

[0032] 107-Middle Casing

[0033] 108- Casing Support Ring

[0034] 200-High-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure 10-Left rotor assembly

[0035] 11-Shaft

[0036] 12-Shaft Front Sealing Ring

[0037] 13-Oil baffle ring

[0038] 14-Outer bearing

[0039] 15-Inner Bearing

[0040] 16-Adapter journal

[0041] 17- Locking nut

[0042] 18-Cover plate

[0043] 19-Interaxial Boss

[0044] 20-Right rotor assembly

[0045] 21-lead conduit

[0046] 30-Left bearing housing assembly

[0047] 31-Left bearing housing

[0048] 32-Sealed Casing

[0049] 33-Bearing housing sealing ring

[0050] 34-Inter-shaft sealing ring

[0051] 35-Outer bearing oil supply ring

[0052] 36-Inner bearing oil supply ring

[0053] 37-Base

[0054] 40-Right bearing housing assembly

[0055] 41-Right bearing housing

[0056] 50-Test Specimen Casing Assembly

[0057] 51-Front Casing

[0058] 52-Inner support ring of the casing

[0059] 53-Middle Casing

[0060] 54-Rear Casing Attached Figure Description

[0061] 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.

[0062] Figure 1 This is a schematic diagram of a rotating disk cavity flow heat transfer test structure in the prior art.

[0063] Figure 2 This is a schematic diagram of the experimental structure for flow heat transfer in the rotating disk cavity of the counter-rotating turbine in this application.

[0064] Figure 3 This is a schematic diagram showing the connection relationship between the rear casing and the right bearing housing in this application. Detailed Implementation

[0065] 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.

[0066] In order to simulate the actual turbine structure and working conditions of aero-engines, this application provides a high-speed real turbine rotating disk cavity flow heat transfer test structure. The test structure consists of two input ends, which provide power input to two rotor assemblies with different speeds. It can meet the requirements of various disk-shaft type rotating heat transfer tests by using different modification parts.

[0067] like Figure 2 As shown, the high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure 200 provided in this application mainly includes a rotor structure and a stator structure. The rotor structure is driven by an electric motor to realize the rotation of the turbine disk. The rotor structure includes two independent left rotor assemblies 10 and right rotor assemblies 20, which are arranged symmetrically from left to right. The stator structure includes a left bearing housing assembly 30, a right bearing housing assembly 40, and a test specimen casing assembly 50. The left / right bearing housing assemblies are fixed to the ground to support the rotating shaft in the rotor assembly and to achieve bearing lubrication. The test specimen casing assembly 50 connects the left and right bearing housing assemblies to realize airflow.

[0068] Since the left rotor assembly 10 and the right rotor assembly 20 have a symmetrical layout, the following embodiments of this application will use the left rotor assembly 10 as an example for explanation, and the right rotor assembly 20 will not be described in detail.

[0069] The left rotor assembly 10 mainly consists of a rotating shaft 11, a front sealing ring 12, an oil baffle ring 13, an outer bearing 14, an inner bearing 15, a transition journal 16, a locking nut 17, and a cover plate 18.

[0070] The rotating shaft 11 is used for connecting and supporting the rotor assembly. The front sealing ring 12, the oil baffle ring 13, and the transition journal 16 are installed on the rotating shaft 11. The front sealing ring 12 and the oil baffle ring 13 are used to restrict the outer bearing 14. The inner bearing 15 is installed on the transition journal 16. The front sealing ring 12 and the transition journal 16 are sealed with the sealing housing 32, the bearing housing sealing ring 33, and the inter-shaft sealing ring 34 in the left bearing housing assembly 30 using a sealing structure to ensure the sealing between the left rotor assembly 10 and the left bearing housing assembly 30.

[0071] The rotating shaft 11 and the adapter journal 16 are connected by a spline. The front end of the adapter journal 16 and the rotating shaft 11 are connected by an inter-shaft boss 19 to ensure the coaxiality of the inner bearing 15. The rear end of the adapter journal 16 is secured by a lock nut 17. In this application, the adapter journal 16 can be fitted with flanges according to different sizes of turbine disks to meet the needs of different tests.

[0072] In a preferred embodiment of this application, the outer bearing 14 is a double-direction angular contact ball bearing, and the inner bearing 15 is a cylindrical roller bearing.

[0073] The cover plate 18 is installed on the inner end of the rotating shaft 11 to maintain the pressure inside the test piece and ensure that the high-temperature gas inside the cavity does not leak. The cover plate 18 can be fixed to the right side of the adapter journal 16 by connecting bolts.

[0074] It should be noted that, unlike the left rotor assembly 10, the right rotor assembly 20 may not include the cover plate 18 but may include the lead wire conduit 21. The lead wire conduit 21 is used to bring out the test leads on the test turbine disk. The cover plate 18 and the lead wire conduit 21 may be added, removed or interchanged depending on the test project.

[0075] The left bearing housing assembly 30 is basically the same as the right bearing housing assembly 40. Therefore, in this embodiment of the application, the left bearing housing assembly 30 is also used as an example for description.

[0076] The left bearing housing assembly 30 mainly consists of a left bearing housing 31, a sealing housing 32, a bearing housing sealing ring 33 and an inter-shaft sealing ring 34, an outer bearing oil supply ring 35, an inner bearing oil supply ring 36 and a base 37.

[0077] The left bearing housing 31 supports the outer bearing 14 and the inner bearing 15. The left bearing housing 31 is integrally machined to ensure the coaxiality of the outer bearing 14 and the inner bearing 15. The outer bearing oil supply ring 35 and the inner bearing oil supply ring 36 are mounted on the left bearing housing 31 and face the outer bearing 14 and the inner bearing 15 respectively, and are used to provide lubricating oil to the bearings.

[0078] The sealing housing 32 is installed at the front end of the left bearing housing 31 to form a sealing structure with the front sealing ring 12. The inter-shaft sealing ring 34 and the outer bearing oil supply ring 35 are installed at the rear end of the left bearing housing 31 to form a sealing structure with the transition journal 16.

[0079] The left bearing housing 31 and the sealing housing 32 are both equipped with air venting seats 38 to provide sealing air venting and ensure that the lubricating oil does not leak.

[0080] The base 37 is cast, which provides support for the left bearing housing 31 while enhancing the rigidity of the fulcrum and suppressing vibration during the test.

[0081] The test specimen casing assembly 50 mainly consists of a front casing 51, an inner support ring 52, a middle casing 53, and a rear casing 54. The front casing 51 is connected to the left bearing seat 31 in the left bearing seat assembly 30, and the rear casing 54 is connected to the right bearing seat 41 in the right bearing seat assembly 40. The casings in the test specimen casing assembly 50 are connected by bolts. Its structure can be designed and modified according to the specific turbine disk structure to meet the test requirements.

[0082] The front casing 51, rear casing 54 and middle casing 53 are equipped with air intake pipes. Air is introduced into the cavity through the air intake pipes on the front casing 51, rear casing 54 and middle casing 53 to simulate the working environment of the turbine disk.

[0083] It should be noted that although the structures of the left bearing housing assembly 30 and the rear bearing housing assembly 40 are basically the same, there are still differences. Specifically, the left bearing housing 31 in the left bearing housing assembly 30 differs from the rear bearing housing 41 in the right bearing housing assembly 40. The left bearing housing 31 is connected to the front casing 51 by bolts, while the rear bearing housing 41 is connected to the rear casing 54 by an axial floating connection. That is, the rear bearing housing 41 and the rear casing 54 are positioned by a flat key 42, and there is a clearance between them. A sealing ring 43 is installed within this clearance, thus forming an axial floating connection structure. Figure 3 As shown, by fixing the left bearing housing assembly 30 to the test specimen housing assembly 50 and axially floating the test specimen housing assembly 50 to the right bearing housing assembly 40, the design requirement of fixing the front / left end and allowing the rear / right end to move axially is achieved. This ensures that the housing can have room to move axially to release thermal stress during the test due to thermal expansion.

[0084] The high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure provided in this application can simulate the actual turbine structure and working conditions of aero-engines, and can also simulate the actual working conditions of counter-rotating turbine disks. The test structure consists of two input ends, which can provide power input to two rotating components with different speeds. This application has strong versatility and can meet the requirements of various disk-shaft type rotating heat transfer tests by using different modification parts.

[0085] 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 high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure, characterized in that, Comprise: The rotor structure and the stator structure, the rotor structure comprises independent left rotor assembly and right rotor assembly, the left rotor assembly and the right rotor assembly are symmetrically arranged, the left rotor assembly and the right rotor assembly all include shaft, shaft front sealing ring, oil retaining ring, outer bearing, inner bearing, adapter journal, locking nut, the shaft front sealing ring, oil retaining ring and adapter journal are installed on the shaft, the shaft front sealing ring and oil retaining ring are used to limit the outer bearing installed on the shaft, the inner bearing is installed on the adapter journal, the shaft front sealing ring and adapter journal are sealed with left bearing seat assembly or right bearing seat assembly through sealing structure, the shaft is connected with adapter journal through spline, wherein the front end of adapter journal is connected with the shaft through the interaxle boss to ensure coaxiality, the rear end of adapter journal is fastened through locking nut, the adapter journal is equipped with flange edge according to different sizes of turbine disc to meet the needs of different tests; The stator structure includes left bearing seat assembly, right bearing seat assembly and test piece machine case assembly, the left bearing seat assembly supports the left rotor assembly, the right bearing seat assembly supports the right rotor assembly, to realize the lubrication of the inner bearing of the rotor assembly, the test piece machine case assembly is connected with the left bearing seat assembly and the right bearing seat assembly, to provide flowing airflow to the disc cavity, to realize the simulation of turbine disc working environment.

2. The high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure of claim 1, wherein, The outer bearing adopts bidirectional angular contact ball bearing, and the inner bearing adopts cylindrical roller bearing.

3. The high-speed counter-rotating turbine rotating disk cavity flow heat transfer test structure of claim 1, wherein, The left rotor assembly and the right rotor assembly further include cover plate or lead wire guide pipe, the cover plate is installed on the inside end of the shaft, to maintain the inner cavity pressure of test turbine disc and ensure that the high-temperature gas in the inner cavity does not leak, and the lead wire guide pipe is used to lead out the test lead wire on the test turbine disc.

4. The high speed contra-rotating turbine rotating disk cavity flow heat transfer test structure of claim 1, wherein, The left bearing seat assembly and the right bearing seat assembly all include bearing seat, sealing machine case, bearing seat sealing ring and interaxle sealing ring, outer bearing oil supply ring, inner bearing oil supply ring and base; The bearing seat is used to support the outer bearing and the inner bearing, and is integrally machined to meet the coaxiality of the outer bearing and the inner bearing; The outer bearing oil supply ring and the inner bearing oil supply ring are installed on the bearing seat and respectively face the outer bearing and the inner bearing, to provide lubricating oil for the bearings; The sealing machine case is installed on the end of the bearing seat, to form a sealing structure with the shaft front sealing ring, and the interaxle sealing ring and the outer bearing oil supply ring are installed on the other end of the bearing seat, to form a sealing structure with the adapter journal; The bearing seat and the sealing machine case are simultaneously provided with air guide seat to provide sealing air and ensure that the lubricating oil does not leak; The base is formed by casting, to provide support for the bearing seat and enhance the fulcrum stiffness to suppress vibration during testing.

5. The high speed contra-rotating turbine rotating disk cavity flow heat transfer test structure of claim 4, wherein, The test piece machine case assembly includes front machine case, machine case inner support ring, middle machine case and rear machine case, the front machine case is connected with the bearing seat in the left bearing seat assembly, the rear machine case is connected with the bearing seat in the right bearing seat assembly, and the front machine case, machine case inner support ring, middle machine case and rear machine case are connected through connecting piece. Wherein, the front machine case, rear machine case and middle machine case are provided with air inlet pipe, to provide air to the cavity of test turbine disc through the air inlet pipe, to realize the simulation of turbine disc working environment.

6. The high rotational speed counter-rotating turbine rotating disk cavity flow heat transfer test structure of claim 5, wherein, The bearing seat in the left bearing seat assembly is connected with the front casing through a connecting piece, and the bearing seat in the right bearing seat assembly is connected with the rear casing in an axial floating connection mode.

7. The high rotational speed counter-rotating turbine rotating disk cavity flow heat transfer test structure of claim 6, wherein, The axial floating connection mode between the bearing seat in the right bearing seat assembly and the rear casing is that the rear bearing seat is positioned with the rear casing through a flat key, and the rear bearing seat and the rear casing have a matching gap therebetween, a sealing ring is arranged in the matching gap, so as to form an axial floating connection structure.

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