Device for testing leakage characteristic between sealing pieces in bearing cavity of aero-engine
By designing a test device to simulate the actual working environment of seals in the bearing cavity of aero engines, the problem of studying the impact of contact length on leakage characteristics is solved, and effective research and analysis of leakage characteristics is achieved.
Patent Information
- Application Number
- CN202421322729.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-12
- Publication Date
- 2025-02-18
- Estimated Expiration
- 2034-06-12
AI Technical Summary
The prior art is difficult to effectively study the impact of contact length on leakage characteristics between seals in the bearing cavity of aero engines.
Design a test device for leakage characteristics between sealed parts in the bearing chamber of an aero engine, including a housing, a central shaft, a first end cover and a second end cover, and simulates the rear bearing chamber of a high-pressure turbine of an aero engine through the coordination of the central shaft and the housing. The actual working environment of the sealing parts inside, adjust the contact position and contact length of the central shaft and the housing to study the impact of the contact length on leakage characteristics.
This test device can simulate the actual working environment with reasonable structure and convenient use. By adjusting the contact position and length, it can effectively study the impact of contact length on the leakage characteristics between seals in the bearing cavity of the aircraft engine.
Smart Images
Figure CN222505740U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of sealing of sealing parts of aircraft engines, and in particular provides a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity, which is used for studying the influence of contact length on the leakage characteristic between sealing parts in an aircraft engine bearing cavity. Background Art
[0002] The comb seal and graphite seal rail in the rear bearing cavity of the high-pressure turbine of the aircraft engine are sealed by tightening bolts, and the graphite seal rail and the rotating shaft are sealed by interference fit. The above two sealing structures can prevent the lubricating oil in the bearing cavity from flowing to another cavity. The above two sealing structures involve two key dimensions: the contact length L1 between the comb seal and the graphite seal rail, and the contact length L2 between the graphite seal rail and the rotating shaft. The design of the above two key dimensions will have a great impact on the leakage characteristics between the seals. Therefore, designing a test device that is convenient for studying the influence of contact length on the leakage characteristics between the seals in the bearing cavity of the aircraft engine has become an urgent problem to be solved. Utility Model Content
[0003] In view of this, the purpose of the utility model is to provide a leakage characteristics test device between sealing parts in aircraft engine bearing cavity, which is used to simulate the actual working environment of aircraft engine bearing cavity sealing parts and study the influence of contact length on the leakage characteristics between sealing parts in aircraft engine bearing cavity.
[0004] The utility model provides a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity, comprising: a shell, a central axis, a first end cover and a second end cover, the shell is cylindrical and a first sealing cavity is arranged in the middle thereof, a first mounting hole is arranged at one end of the first sealing cavity, a second mounting hole and air holes evenly arranged along the circumference of the second mounting hole are arranged at the other end of the first sealing cavity, the central axis comprises a cylindrical head and a fastening rod connected to the cylindrical head, the cylindrical head is provided with a step structure along its circumference, the step structure is used for sealing connection with the inner circumferential wall surface of the first mounting hole and / or the outer end wall surface of the first mounting hole, the fastening rod cooperates with the second mounting hole and a fastening nut is installed at the end, the first end cover and the second end cover are respectively sealed and installed at the two ends of the shell, the first end cover is provided with an air inlet hole connected to an air supply system, the second end cover is provided with an air outlet hole, and a flow meter is connected to the air outlet hole.
[0005] Preferably, the first end cover and the second end cover are both sealed and mounted on both ends of the shell by nuts and screws.
[0006] Further preferably, a sealing gasket is provided between the first end cover and the shell, and between the second end cover and the shell.
[0007] Further preferably, the leakage characteristics test device between sealing parts in the aircraft engine bearing cavity also includes a base, and the shell is fixedly installed on the base.
[0008] Further preferably, an inverted trapezoidal groove structure is provided above the base, and the shell is cooperatively arranged in the inverted trapezoidal groove structure and fixed by pins.
[0009] Further preferably, a pressure sensor is installed on the first end cover for detecting the intake pressure.
[0010] The utility model provides a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity, which has a reasonable structure and is easy to use. The actual working environment of the sealing parts in the rear bearing cavity of a high-pressure turbine of an aircraft engine can be simulated through the cooperation of the central shaft and the shell. During the test, the influence of the contact length at different contact positions on the leakage characteristics between the sealing parts in the bearing cavity of an aircraft engine can be studied by adjusting the contact position and contact length between the central shaft and the shell. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] The present invention is further described in detail below with reference to the accompanying drawings and implementation modes:
[0012] Figure 1 A three-dimensional diagram of a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity provided by the present invention;
[0013] Figure 2 An exploded view of a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity provided by the present invention;
[0014] Figure 3 A cross-sectional view of a test device for leakage characteristics between sealing parts in an aircraft engine bearing cavity provided by the invention;
[0015] Figure 4 Schematic diagram of the structure of the central axis;
[0016] Figure 5 It is a first connection schematic diagram of the step structure of the cylindrical head and the first mounting hole;
[0017] Figure 6 is a schematic diagram of a second connection between the step structure of the cylindrical head and the first mounting hole;
[0018] Figure 7 It is a schematic diagram of the third connection between the step structure of the cylindrical head and the first mounting hole. DETAILED DESCRIPTION
[0019] The present invention will be further explained below in conjunction with specific implementation schemes, but the present invention is not limited thereto.
[0020] like Figures 1 to 7 As shown, the utility model provides a leakage characteristic test device between sealing parts in an aircraft engine bearing cavity, comprising: a shell 1, a central axis 2, a first end cover 3 and a second end cover 4, the shell 1 is cylindrical and a first sealed cavity is arranged in the middle thereof, one end of the first sealed cavity is provided with a first mounting hole, the other end of the first sealed cavity is provided with a second mounting hole and an air hole 13 uniformly arranged along the circumference of the second mounting hole, the central axis 2 comprises a cylindrical head 21 and a fastening rod 22 connected to the cylindrical head 21, the cylindrical head 21 is provided with a step structure 211 along its circumference, the step structure 211 is used to be sealed and connected with the inner circumferential wall surface of the first mounting hole and / or the outer end wall surface of the first mounting hole, the fastening rod 22 cooperates with the second mounting hole and a fastening nut 23 is installed at the end, the first end cover 3 and the second end cover 4 are respectively sealed and installed at the two ends of the shell 1, the first end cover 3 is provided with an air inlet 31 connected to the air supply system, the second end cover 4 is provided with an air outlet 41, and the air outlet 41 is connected with a flow meter.
[0021] The leakage characteristics test device between sealing parts in the bearing cavity of an aircraft engine can simulate the actual working environment of the sealing parts in the rear bearing cavity of a high-pressure turbine of an aircraft engine through the cooperation of the central shaft and the shell. During the test, the influence of the contact length at different contact positions on the leakage characteristics between the sealing parts in the bearing cavity of an aircraft engine can be studied by adjusting the contact position and contact length between the central shaft and the shell. There are two contact positions, the first one is the inner peripheral wall surface of the first mounting hole, and the second one is the outer end wall surface of the first mounting hole. There are three contact modes at the two contact positions: the step structure is only sealed with the outer end wall surface of the first mounting hole (such as Figure 5 The step structure is only sealed with the inner wall of the first mounting hole (as shown); Figure 6 The step structure is sealed with the outer end wall of the first mounting hole and the inner peripheral wall of the first mounting hole (as shown); Figure 7 shown).
[0022] During the test, fix the shell and install the middle shaft. By selecting middle shafts of different sizes and adjusting the fastening nuts on the fastening rods, different contact positions and contact lengths are simulated. Then, fix the two end covers, connect the first end cover to the air supply system, and connect the second end cover to the flow meter to test the leakage characteristics.
[0023] As an improvement of the technical solution, the first end cover 3 and the second end cover 4 are both sealed and installed at the two ends of the shell 1 by nuts and screws. Preferably, the nuts and screws are evenly arranged along the circumference of the first end cover and the second end cover.
[0024] As an improvement of the technical solution, Figure 2As shown, a sealing gasket 5 is provided between the first end cover 3 and the shell 1 and between the second end cover 4 and the shell 1 to enhance the sealing effect. Preferably, the sealing gasket is a polytetrafluoroethylene gasket, which has good corrosion resistance, good self-lubrication and wear resistance, and a temperature resistance of 250°C.
[0025] As an improvement of the technical solution, Figure 1 , Figure 2 As shown, the leakage characteristic test device between sealing parts in the aircraft engine bearing cavity also includes a base 6, and the housing 1 is fixedly installed on the base 6.
[0026] As an improvement of the technical solution, Figure 1 , Figure 2 As shown, an inverted trapezoidal groove structure is arranged above the base 6, and the shell 1 is arranged in the inverted trapezoidal groove structure and fixed by pins. The base can ensure the balance of the test device during the experiment and prevent the impact force generated by the ventilation moment from causing unnecessary influence on the device.
[0027] As an improvement of the technical solution, a pressure sensor is installed on the first end cover 3 (which can be installed on Figure 1 The hole numbered 32 in the middle is used to detect the intake pressure.
[0028] The specific implementation methods of the present utility model are written in a progressive manner, emphasizing the differences between the various implementation methods, and the similar parts thereof can be referenced to each other.
[0029] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.
Claims
1. A leakage characteristic test device between sealing parts in the bearing cavity of an aircraft engine, characterized in that: include: A shell (1), a central axis (2), a first end cover (3) and a second end cover (4); the shell (1) is cylindrical and has a first sealed cavity in the middle thereof; one end of the first sealed cavity is provided with a first mounting hole; the other end of the first sealed cavity is provided with a second mounting hole and air holes (13) uniformly arranged along the circumference of the second mounting hole; the central axis (2) comprises a cylindrical head (21) and a fastening rod (22) connected to the cylindrical head (21); the cylindrical head (21) is provided with a step structure (211) along its circumference; the step structure (211) is provided with a first mounting hole; the second mounting hole (212) is provided with a second mounting hole and air holes (13) uniformly arranged along the circumference of the second mounting hole; the central axis (2) comprises a cylindrical head (21) and a fastening rod (22) connected to the cylindrical head (21); the cylindrical head (21) is provided with a step structure (211) along its circumference; the step structure (212) is provided with a first mounting hole; the second mounting hole (212) is provided with a second mounting hole and air holes (13) uniformly arranged along the circumference of the second mounting hole; the cylindrical head (21) is provided with a first mounting hole and an air hole ... The step structure (211) is used for sealing connection with the inner peripheral wall surface of the first mounting hole and / or the outer end wall surface of the first mounting hole, the fastening rod (22) cooperates with the second mounting hole and a fastening nut (23) is installed at the end thereof, the first end cover (3) and the second end cover (4) are respectively sealed and installed at the two ends of the shell (1), the first end cover (3) is provided with an air inlet (31) connected to the air supply system, and the second end cover (4) is provided with an air outlet (41), and the air outlet (41) is connected to a flow meter.
2. The leakage characteristics test device between sealing parts in the bearing cavity of an aircraft engine according to claim 1, characterized in that: The first end cover (3) and the second end cover (4) are both sealed and mounted on both ends of the housing (1) by means of nuts and screws.
3. The leakage characteristics test device between sealing parts in the bearing cavity of an aircraft engine according to claim 1, characterized in that: A sealing gasket (5) is provided between the first end cover (3) and the shell (1), and between the second end cover (4) and the shell (1).
4. The leakage characteristics test device between sealing parts in the bearing cavity of an aircraft engine according to claim 1, characterized in that: It also comprises a base (6), and the shell (1) is fixedly mounted on the base (6).
5. The leakage characteristics test device between sealing parts in the bearing cavity of an aircraft engine according to claim 4, characterized in that: An inverted trapezoidal groove structure is arranged above the base (6), and the housing (1) is arranged in the inverted trapezoidal groove structure and fixed by pins.
6. The leakage characteristics test device between seals in the bearing cavity of an aircraft engine according to claim 1, characterized in that: A pressure sensor is installed on the first end cover (3) for detecting the intake pressure.