Aeroengine Core Test Facility

Abstract

An aeroengine core test device is used for the performance test of the core under a clean flow path, and includes a test stand, a cover plate, a first sealing structure and a second sealing structure. The test stand, the cover plate, the first sealing structure and the second sealing structure limit a closed cavity filled with lubricating oil around the journal of the core. The present invention provides a cavity for the front support bearing of the engine core to accommodate lubricating oil, which can protect parts, reduce the replacement workload during the test, and improve the test efficiency.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engines, and particularly relates to a test device for a core engine of an aero-engine. Background Art

[0002] The high-pressure part of an aero-engine, also known as the core engine, is the most important component of an aero-engine. Conducting new development work of an aero-engine based on the core engine can greatly shorten the R & D cycle, and several derivative aero-engine whole-machine models can be quickly developed according to a successfully verified core engine. The verification tests of an aero-engine core engine include dynamic stress tests of the core engine rotor, performance tests of the core engine under a clean flow path, and engine whole-machine stringing tests, etc. During this period, the test device needs to be modified and replaced many times.

[0003] In the stage of dynamic stress test of the rotor, it is necessary to modify the engine journal and install a transfer shaft. The sealing structure of the transfer shaft serves as the sealing structure of the front support point of the core engine, providing lubricating oil for the bearing cavity to lubricate and cool the front support bearing; while in the subsequent performance test of the core engine under a clean flow path, the transfer shaft is removed, and there is no corresponding sealing structure at the front support point of the core engine. Without lubricating oil, the core engine cannot operate, and it is necessary to additionally install lubricating and cooling devices, increasing the test cost and workload. Summary of the Invention

[0004] The present invention provides a test device for an aero-engine core engine, aiming to provide a sealing structure for the front support point of the core engine during the performance test of the engine under a clean flow path, so that the front support bearing can be lubricated and cooled by lubricating oil during the test process, reducing the replacement work during the stringing of the core engine with the whole machine and improving the test reliability.

[0005] A test device for an aero-engine core engine includes a test bench, and further includes a cover plate, a first sealing structure, and a second sealing structure; the cover plate is installed on the test bench at the front end of the core engine, and has a through hole for a part of the journal of the core engine under test to pass through. The first sealing structure is arranged between the cover plate and the journal, and the second sealing structure is arranged at the connection between the cover plate and the test bench; the cover plate, the test bench, the first sealing structure, and the second sealing structure jointly define an annular closed cavity around the journal, and the closed cavity is filled with lubricating oil to provide lubrication for the front support bearing of the core engine under test.

[0006] The test device provided by the present invention can provide a sealing structure for the front support point of the core engine during the performance test of the core engine under a clean flow path, form a closed cavity accommodating the front support bearing, and the lubricating oil in the cavity can lubricate and cool the front support bearing, simplifying the supporting test equipment and avoiding excessive wear of the parts under test during the test.

[0007] Preferably, the first sealing structure includes a sealing nut installed on the journal and a sealing ring matching therewith on the cover plate, and the sealing ring protrudes relative to the installation plane of the cover plate.

[0008] Optionally, the sealing nut is a labyrinth nut, the sealing ring is a coating structure matching therewith, and the first sealing structure is a labyrinth sealing structure formed by the matching of the two, which can seal the closed cavity in a non-contact form, prevent lubricating oil from leaking out and avoid part wear at the same time.

[0009] Optionally, the sealing nut is a labyrinth nut, the sealing ring is a honeycomb structure matching therewith, and the first sealing structure is a honeycomb sealing structure formed by the matching of the two, which can seal the closed cavity in a non-contact form, prevent lubricating oil from leaking out and avoid part wear at the same time.

[0010] Preferably, the sealing nut is a general part for the overall engine assembly, and its model and size are both universal with the connection part of the low-pressure rotor during the overall engine assembly, and it can be directly assembled and connected, avoiding part replacement and reducing test procedures.

[0011] Preferably, the second sealing structure includes an annular installation boss on the cover plate that matches the test bench, and a groove is provided on the contact surface between the boss and the test bench, and a sealing part is installed in the groove.

[0012] Optionally, the second sealing structure uses a metal sealing ring.

[0013] Optionally, the second sealing structure uses a rubber oil seal.

[0014] Preferably, the test bench includes a detachable front bearing frame that can be removed during subsequent overall engine assembly tests, and the cover plate is installed on the front bearing frame. After completing the core engine performance test under a clean flow path, directly remove the front bearing frame and the cover plate together, simplify the modification process, and avoid part interference in subsequent tests.

[0015] Preferably, the front bearing frame is provided with an installation interface for the support of the slip ring device for the dynamic stress test of the core engine rotor. The front bearing frame is configured as a support for the dynamic stress test of the rotor, and the slip ring device can be installed through the support during the dynamic stress test of the rotor, reducing the replacement workload during modification. Description of the Drawings

[0016] Figure 1 is a schematic structural diagram of an aeroengine core engine test device;

[0017] Figure 2 is a schematic cross-sectional structural diagram of the front support point position of the aeroengine core engine test device;

[0018] Figure 3 It is a schematic installation diagram for the rotor dynamic stress test phase.

[0019] The above-mentioned drawings are for a more detailed description of the technical concept of the present invention. Only the technical information related to the present invention is schematically described in the drawings, and all the parts and equipment involved are not drawn strictly to scale. The above-mentioned drawings do not constitute a specific limitation on the implementation mode of the present invention.

[0020] Meanings of the reference numerals:

[0021] 1 - Core engine; 2 - Test stand; 3 - Front support bearing; 4 - Journal; 5 - Cover plate; 6 - First sealing structure; 7 - Second sealing structure; 8 - Front bearing frame; 9 - Sealing ring; 10 - Sealing nut; 11 - Boss; 12 - Sealing part; 13 - Bolt; 14 - Front support bearing cavity; 15 - Slip ring support; 16 - Slip ring adapter shaft; 17 - Bolt. Specific embodiments

[0022] The following further describes the technical concept of the present invention through embodiments in conjunction with the drawings.

[0023] The verification test of the aero - engine core engine includes test items such as rotor dynamic stress test, core engine performance test under a clean flow path, and engine overall assembly. During the rotor dynamic stress test phase, a slip ring device needs to be installed to test the rotor dynamic stress; during the core engine performance test phase under a clean flow path, the slip ring device is removed; during the engine overall assembly phase, the front end of the core engine needs to be connected and assembled with the low - pressure rotor part for overall performance testing.

[0024] According to an embodiment of the present invention, as Figure 1 shown, during the core engine performance test phase under a clean flow path, the aero - engine core engine test device is installed and completed, including the core engine 1, the test stand 2, and the cover plate 5. The test stand 2 includes the front bearing frame 8, and the circular cover plate 5 is installed on the front bearing frame 8 through a plurality of bolts 13 circumferentially arranged on the edge. A sealing ring 9 protrudes on the cover plate 5, and a first sealing structure 6 is arranged at the contact position with the journal 4; a second sealing structure 7 is arranged at the contact position between the cover plate 5 and the front bearing frame 8; the cover plate 5, the front bearing frame 8, the first sealing structure 6, and the second sealing structure 7 jointly define a closed front support bearing cavity 14 around the journal 4. The front support bearing cavity 14 is filled with lubricating oil, which lubricates and cools the front support bearing 3 located therein.

[0025] Among them, the sealing nut 10 is a labyrinth nut, the sealing ring 9 is a coated structure, and together with the sealing nut 10, it forms a labyrinth sealing structure, which realizes sealing at the first sealing structure 6 in a non - contact manner to prevent the leakage of the lubricating oil in the front support bearing cavity 14.

[0026] According to another embodiment, the sealing ring 9 is a honeycomb structure, which forms a honeycomb sealing structure with the sealing nut 10, and realizes sealing at the first sealing structure 6 in a non-contact manner to prevent the lubricating oil in the front support bearing cavity 14 from leaking.

[0027] The cover plate 5 is provided with a boss 11 that matches the front bearing frame 8. The cover plate 5 is installed on the front bearing frame 8 by clamping with the boss 11. A groove is provided on the contact surface between the boss 11 and the front bearing frame 8, and a sealing member 12 is installed in the groove. The sealing member 12 is a metal sealing ring.

[0028] According to another embodiment, the sealing member 12 is a rubber oil seal.

[0029] According to still another embodiment, the sealing ring 9 is set as a detachable independent part and is fixed on the cover plate 5 by bolts to facilitate the overhaul and maintenance of the test system during the test process.

[0030] Figure 3 The installation state of relevant parts during the rotor dynamic stress test stage is shown. The slip ring adapter shaft 16 is installed on the journal 4 and is fixedly installed on the front bearing frame 8 through the slip ring support 15 by circumferentially arranged bolts 17. The front bearing frame 8 can be structurally matched with the slip ring support 15. After the rotor dynamic stress test is completed, only the slip ring support 15 and the slip ring adapter shaft 16 need to be removed, and parts such as the cover plate 5 are installed and assembled to Figure 2 the state shown. During the process, the bench parts such as the front bearing frame 8 do not need to be replaced. After the core engine performance test under a clean flow path is completed, only the front bearing frame 8 together with the cover plate 5 needs to be directly removed, and the sealing nut 10 fixed on the journal 4 is a general part for the whole machine string assembly and can be directly matched with the low-pressure rotor, reducing the requirements for replacement procedures and spare parts.

[0031] It should be understood that the above embodiments are for further detailed description of the technical concept of the present invention so that those skilled in the art can understand, and do not constitute specific limitations on the implementation manners of the present invention. Within the protection scope of the claims, improvements or equivalent replacements made to the structures involved in the present invention, and the combination of each embodiment without structural interference, all fall within the protection scope of the present invention.

Claims

1. An aero-engine core rig test device, including a test stand, characterized in that: The aero-engine core rig test device further includes a cover plate, a first sealing structure and a second sealing structure; The cover plate is installed on the test stand at the front end of the core rig to be tested, and has a through hole for a part of the journal of the core rig to be tested to pass through; The first sealing structure is arranged between the cover plate and the journal, and the second sealing structure is arranged at the connection between the cover plate and the test stand; The cover plate, the test stand, the first sealing structure and the second sealing structure jointly define an annular closed cavity around the journal, and the closed cavity is filled with lubricating oil to lubricate the front support bearing of the core rig to be tested located in the closed cavity; Wherein, the first sealing structure includes a sealing nut installed on the journal and a sealing ring matching with it on the cover plate, and the sealing ring protrudes relative to the installation plane of the cover plate; The second sealing structure includes an annular installation boss on the cover plate that matches the test stand, and a groove is arranged on the contact surface between the boss and the test stand, and a sealing member is installed in the groove; 2. The aeroengine core test device according to claim 1, characterized in that The sealing nut is a labyrinth nut, and the sealing ring is a coating structure matching with it; 3. The aero-engine core rig test device according to claim 1, characterized in that, The sealing nut is a labyrinth nut, and the sealing ring is a honeycomb structure matching with it; 4. The aeroengine core engine test device according to claim 1 or 2 or 3, characterized in that, The sealing nut is a general part for the overall engine assembly; 5. The aero-engine core test device according to claim 1, characterized in that The sealing member is a metal sealing ring; 6. The aeroengine core engine test device according to claim 4, characterized in that, The sealing member is a rubber oil seal; 7. The aero-engine core test device according to claim 1, characterized in that The test stand includes a detachable front bearing frame that can be removed during the overall engine assembly, and the cover plate is installed on the front bearing frame; 8. The aviation engine core engine test device according to claim 7, wherein, The front bearing frame is provided with an installation interface for the support of the dynamic stress test slip ring device of the core rig rotor.

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