CN113899558A - Aero-engine double-rotor system rub-impact test device - Google Patents
Aero-engine double-rotor system rub-impact test device Download PDFInfo
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- CN113899558A CN113899558A CN202111170120.2A CN202111170120A CN113899558A CN 113899558 A CN113899558 A CN 113899558A CN 202111170120 A CN202111170120 A CN 202111170120A CN 113899558 A CN113899558 A CN 113899558A
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- 238000009863 impact test Methods 0.000 title claims description 8
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 230000003068 static effect Effects 0.000 claims abstract description 8
- 238000012360 testing method Methods 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 36
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 3
- 230000004044 response Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a collision and friction test device for a birotor system of an aircraft engine, which comprises a low-pressure rotor, a high-pressure rotor, a low-pressure compressor support, a high-pressure turbine support, an intermediate bearing, a low-pressure rotor coupling, a high-pressure rotor coupling, a transmission gear box, an inner culvert casing and an outer culvert casing. The invention keeps the main structural components of the aero-engine, and can arrange corresponding measuring points on the high-low pressure rotor and the casing, thereby being capable of measuring the unbalanced response of the dual-rotor system of the aero-engine, the fault characteristic of the intermediate bearing and the static-rotating rubbing fault characteristic of the aero-engine. The dynamic characteristics of the aero-engine under the condition of full-circumference rub-impact of the blades and the stators of the dual-rotor wheel disc of the aero-engine are simulated by installing the clamping ring type rub-impact body with the slope on the casing and pressing in the cylinder through the hydraulic device to adjust the static clearance.
Description
Technical Field
The invention belongs to the field of mechanical testing, and particularly relates to a rub-impact test device for a dual-rotor system of an aircraft engine.
Background
The aircraft engine is the power source of the aircraft, and the reliability of the aircraft engine directly influences the safe flight of the aircraft. With the rapid development of the aviation industry in China, in order to pursue high speed and high thrust-weight ratio, the aircraft engine mostly adopts a dual-rotor structure, namely a structure that a low-pressure rotor rotating shaft penetrates through a high-pressure rotor rotating shaft, and the high-pressure rotating shaft and the low-pressure rotating shaft are connected through an intermediate bearing. Besides the double-rotor structure, the aircraft engine has blades on the double rotors, and the double rotors are supported on the casing, so that the blades of the double rotors may collide with the stator casing during the operation of the aircraft engine. However, the structure of the aircraft engine is complex, and the vibration sources are many, which brings corresponding difficulties for fault monitoring of the aircraft engine. Therefore, the working mechanism of the aero-engine is clarified, and the running state of the key part is monitored, so that the method is very important for fault diagnosis of the aero-engine.
The prior art is that the rubbing body is clamped on the casing, so that only the rubbing fault of the fixing material under the fixed static clearance can be measured, the local rubbing condition can be simulated, and the replacement of the rubbing body is troublesome.
Disclosure of Invention
The invention aims to solve the technical problems and further provides a lubricating oil thermal cycle measuring system for a bearing of an engine experiment table.
The invention relates to a collision and friction test device for a birotor system of an aircraft engine, which comprises a low-pressure rotor 16, a high-pressure rotor 17, a low-pressure compressor support 2, a high-pressure compressor support 6, a high-pressure turbine support 10, an intermediate bearing 13, a low-pressure rotor coupling 1, a high-pressure rotor coupling 8, a transmission gear box 9, an inner culvert casing 5 and an outer culvert casing 3;
the low pressure rotor 16 is connected with the motor through a low pressure compressor coupler 1, the high pressure rotor 17 is sleeved on a rotating shaft of the low pressure rotor 16, supported on the low pressure rotor 16 through an intermediate bearing 13 and can be connected with the motor through a high pressure rotor coupler 8 and a transmission gear box 9; the low-pressure rotor 16 is supported on the culvert casing 3 through a low-pressure compressor support 2, the high-pressure rotor 17 is supported on the culvert casing 5 through a high-pressure compressor support 6 and a high-pressure turbine support 10, and the culvert casing 3 is supported on a rigid base;
the low-pressure rotor 16 comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the low-pressure compressor blades 4 and the low-pressure turbine blades 12 through bolts, a sealing labyrinth 20 is arranged on each rotating disc, and the outward extension of the sealing labyrinth 20 is adjusted through bolts and gaskets; the high-pressure rotor 17 comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the high-pressure compressor blades 7 and the high-pressure turbine blades 11 through bolts, and the rotating discs are provided with sealing labyrinth teeth 20.
Further, the culvert casing 5 is embedded with a rubbing body B15 and a rubbing body C18 along the axial direction, and the positions are adjusted through the axial embedding amount, so that the rubbing gap is controlled; the outer culvert casing 3 is embedded with a rubbing body A14 and a rubbing body D21, and the position is adjusted by the axial embedding amount so as to control the rubbing gap; the local rubbing device 22 is arranged on the culvert casing 3 and is connected with a rubbing device main body 26 through a fixing bolt 25, a screw-in bolt 24 is arranged in the rubbing device main body 26, the screw-in bolt 24 is controlled to screw in or screw out through an external stepping motor, and then the feeding amount of the rubbing ejector rod 27 is controlled.
Further, the collision and massage body A14, the collision and massage body B15, the collision and massage body C18 and the collision and massage body D21 are all annular and are connected to the culvert casing 3 and the culvert casing 5, the collision and massage body A14, the collision and massage body B15, the collision and massage body C18 and the collision and massage body D21 are all provided with slopes, and when the collision and massage body is pressed in the axial direction by using a hydraulic device, the clearance between the rotor blade and the culvert casing 3 or the culvert casing 5 is reduced.
Further, the side surface of the culvert casing 3 is provided with a hole and a local rubbing device 23, the local rubbing device 23 comprises a motor precession bolt 24, a fixing bolt 25, a rubbing device main body 26 and a rubbing ejector rod 27, the motor precession bolt 24 abuts against the rubbing ejector rod 27 to advance into the culvert casing 3 through a stepping motor, so that the clearance between a rotor and a stator of the low-pressure compressor blade 4 is reduced, and the reduction of the rotating static clearance is equal to the advancing amount of the rubbing ejector rod.
Furthermore, a sealing labyrinth 20 is fixed at the rotary table 22, the position of the sealing labyrinth along the axial direction is changed by increasing or decreasing gaskets between the sealing labyrinth 20 and the rotary table 22, a sealing stator 19 at the corresponding position of the sealing labyrinth is a slope device, and the gap between the sealing labyrinth and the sealing stator is reduced by increasing the gaskets.
Advantageous effects
The device has a structure similar to that of a real aero-engine, particularly an intermediate bearing and a casing, can further reflect the dynamic characteristics of the aero-engine, and simultaneously has various rubbing parts, so that rubbing of the double-rotor wheel disc blade and the casing and rubbing of the sealing labyrinth disc and the casing can be performed, not only can local point rubbing simulation be performed, but also the condition of full-circumference rubbing can be simulated, meanwhile, a rubbing body is convenient to replace, and the static clearance can be adjusted. The dynamic characteristics of the aeroengine under various rubbing faults can be reflected. The whole structure is scientific, easy to process, convenient to disassemble and assemble and easy to popularize.
The invention keeps the main structural components of the aero-engine, and can arrange corresponding measuring points on the high-low pressure rotor and the casing, thereby being capable of measuring the unbalanced response of the dual-rotor system of the aero-engine, the fault characteristic of the intermediate bearing and the static-rotating rubbing fault characteristic of the aero-engine. The dynamic characteristics of the aero-engine under the condition of full-circumference rub-impact of the blades and the stators of the dual-rotor wheel disc of the aero-engine are simulated by installing the clamping ring type rub-impact body with the slope on the casing and pressing in the cylinder through the hydraulic device to adjust the static clearance.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the position of the local rubbing device according to the present invention;
FIG. 3 is a schematic view of a partial rubbing device according to the present invention.
The reference numbers are as follows:
the device comprises a low-pressure compressor coupling 1, a low-pressure compressor support 2, a culvert casing 3, a culvert casing 4, a culvert casing 5, a high-pressure compressor support 6, a high-pressure compressor blade 7, a high-pressure rotor coupling 8, a transmission gear box 9, a high-pressure rotor turbine support 10, a high-pressure turbine blade 11, a low-pressure turbine blade 12, an intermediate bearing 13, a rubbing body A14, a rubbing body B15, a low-pressure rotor 16, a high-pressure rotor 17, a rubbing body C18, a sealing stator 19, a sealing labyrinth 20, a rubbing body D21, a rubbing body D22, a rotating disc, a local rubbing device 23, a motor precession bolt 24, a fixing bolt 25, a rubbing device main body 26 and a rubbing ejector rod 27.
Detailed Description
The present embodiment will be specifically described below with reference to fig. 1 to 3.
The invention relates to a rub-impact test device for a birotor system of an aircraft engine, which comprises a low-pressure rotor 16, a high-pressure rotor 17, a low-pressure compressor support 2, a high-pressure compressor support 6, a high-pressure turbine support 10, an intermediate bearing 13, a low-pressure rotor coupling 1, a high-pressure rotor coupling 8, a transmission gear box 9, an inner culvert casing 5 and an outer culvert casing 3. The low pressure rotor 16 is connected with the motor through a low pressure compressor coupler 1, and the high pressure rotor 17 is sleeved on the rotating shaft of the low pressure rotor 16, supported on the low pressure rotor 16 through an intermediate bearing 13 and can be connected with the motor through a high pressure rotor coupler 8 and a transmission gear box 9. The low-pressure rotor 16 is supported on the culvert casing 3 through the low-pressure compressor support 2, the high-pressure rotor 17 is supported on the culvert casing 5 through the high-pressure compressor support 6 and the high-pressure turbine support 10, and the culvert casing 3 is supported on the rigid base.
The low-pressure rotor 16 comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the low-pressure compressor blades 4 and the low-pressure turbine blades 12 through bolts, a sealing labyrinth 20 is arranged on each rotating disc, and the outward extension of the sealing labyrinth 20 is adjusted through bolts and gaskets; the high-pressure rotor 17 comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the high-pressure compressor blades 7 and the high-pressure turbine blades 11 through bolts, and the rotating discs are provided with sealing labyrinth teeth 20. The connotative casing 5 is embedded with a rubbing body B15 and a rubbing body C18 along the axial direction, and the positions are adjusted through the axial embedding amount, so that the rubbing gap is controlled; the outer culvert casing 3 is embedded with a rubbing body A14 and a rubbing body D21, and the position is adjusted by the axial embedding amount so as to control the rubbing gap; the local rubbing device 22 is arranged on the culvert casing 3 and is connected with a rubbing device main body 26 through a fixing bolt 25, a screw-in bolt 24 is arranged in the rubbing main body 26, the screw-in bolt 24 is controlled to screw in or screw out through an external stepping motor, the feeding amount of a rubbing ejector rod 27 is further influenced, and the rubbing gap is controlled. The utility model discloses a collision and massage body A14, collision and massage body B15, collision and massage body C18, collision and massage body D21 are the annular, connect on outer culvert machine casket 3 and inner culvert machine casket 5, all have the slope on collision and massage body A14, collision and massage body B15, collision and massage body C18, the collision and massage body D21, when application hydraulic means pressed the collision and massage body along the axial, rotor blade and outer culvert machine casket 3 or inner culvert machine casket 5's clearance will reduce, and the clearance volume that reduces is relevant with the distance that the axial was impressed to confirm static clearance.
The side face of the culvert casing 3 is provided with a hole and a local rubbing device 23, the local rubbing device 23 comprises a motor precession bolt 24, a fixing bolt 25, a rubbing device main body 26 and a rubbing ejector rod 27, the motor precession bolt 24 abuts against the rubbing ejector rod 27 to move towards the inside of the culvert casing 3 through a stepping motor, so that the clearance between a rotor and a stator of the low-pressure compressor blade 4 is reduced, and the reduction of the static clearance is equal to the movement of the rubbing ejector rod. The sealing labyrinth 20 is fixed on the rotary table 22, the axial position of the sealing labyrinth is changed by increasing or decreasing gaskets between the sealing labyrinth 20 and the rotary table 22, the sealing stator 19 at the corresponding position of the sealing labyrinth is a slope device, and the clearance between the sealing labyrinth and the sealing stator is reduced by increasing the gaskets.
Description of installation
The low-pressure rotor 15 is provided with a rotating shaft and two rotating discs, wherein the two rotating discs are respectively connected with the low-pressure compressor blades 4 and the low-pressure turbine blades 11 through bolts, each rotating disc is provided with a sealing labyrinth 18, and the outward extension of the sealing labyrinth can be adjusted through bolts and gaskets. The high-pressure rotor 16 also has a rotating shaft and two rotating discs, wherein the two rotating discs are respectively connected with the high-pressure compressor blades 7 and the high-pressure turbine blades 10 through bolts, and each rotating disc is also provided with a sealing labyrinth 18. The low pressure rotor 15 is connected with the motor through the low pressure compressor coupler 1, the high pressure rotor 16 is sleeved on the low pressure rotor 15 rotating shaft and supported on the low pressure rotor 15 through the intermediary bearing 12, and can be connected with the motor through the high pressure rotor coupler and the transmission gear box 8. The low-pressure rotor 15 is supported on the culvert casing 3 through the low-pressure compressor support 2, and the high-pressure rotor 16 is supported on the culvert casing 5 through the high-pressure compressor support 6 and the high-pressure turbine support 9.
The inner culvert casing 5 can be embedded with a rubbing body B14 and a rubbing body C17 along the axial direction, and the positions can be adjusted by the axial embedding amount so as to control the rubbing gap. The outer culvert casing 3 can be embedded with a rubbing body A13 and a rubbing body D19, and the positions can be adjusted by the axial embedding amount so as to control the rubbing gap.
The local rubbing device 20 is located on the culvert casing 3 and is connected with the rubbing device main body 23 through the fixing bolt 22, the rubbing main body 23 is internally provided with a precession bolt 21, the precession bolt 21 can be controlled to be screwed in or out through an external stepping motor, the feeding amount of the rubbing ejector rod 24 is further influenced, and the rubbing gap is controlled.
The above-mentioned embodiments are only preferred embodiments of the present invention, and are not intended to limit the embodiments of the present invention, and those skilled in the art can easily make various changes and modifications according to the main concept and spirit of the present invention, so the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. The collision and friction test device for the dual-rotor system of the aircraft engine is characterized by comprising a low-pressure rotor (16), a high-pressure rotor (17), a low-pressure compressor support (2), a high-pressure compressor support (6), a high-pressure turbine support (10), an intermediate bearing (13), a low-pressure rotor coupling (1), a high-pressure rotor coupling (8), a transmission gear box (9), an inner culvert casing (5) and an outer culvert casing (3);
the low-pressure rotor (16) is connected with the motor through a low-pressure compressor coupler (1), the high-pressure rotor (17) is sleeved on a rotating shaft of the low-pressure rotor (16) and supported on the low-pressure rotor (16) through an intermediate bearing (13), and the high-pressure rotor can be connected with the motor through a high-pressure rotor coupler (8) and a transmission gear box (9); the low-pressure rotor (16) is supported on the culvert casing (3) through a low-pressure compressor support (2), the high-pressure rotor (17) is supported on the culvert casing (5) through a high-pressure compressor support (6) and a high-pressure turbine support (10), and the culvert casing (3) is supported on a rigid base;
the low-pressure rotor (16) comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the low-pressure compressor blades (4) and the low-pressure turbine blades (12) through bolts, a sealing labyrinth (20) is arranged on each rotating disc, and the outward extension of the sealing labyrinth (20) is adjusted through bolts and gaskets; the high-pressure rotor (17) comprises a rotating shaft and two rotating discs, the two rotating discs are respectively connected with the high-pressure compressor blades (7) and the high-pressure turbine blades (11) through bolts, and the rotating discs are provided with sealing labyrinth teeth (20).
2. The aircraft engine dual-rotor system rub-impact test device according to claim 1, wherein the culvert casing (5) is axially embedded with rub-impact bodies B (15) and C (18), and the position of the culvert casing is adjusted by the axial embedding amount, so that rub-impact clearance is controlled; the outer culvert casing (3) is embedded with a rubbing body A (14) and a rubbing body D (21), and the positions are adjusted through the axial embedding amount so as to control the rubbing gap; the local rubbing device (22) is arranged on the outer culvert casing (3) and is connected with a rubbing device main body (26) through a fixing bolt (25), a screwing-in bolt (24) is arranged in the rubbing device main body (26), the screwing-in bolt (24) is controlled to screw in or screw out through an external stepping motor, and then the feeding amount of a rubbing ejector rod (27) is controlled.
3. The aircraft engine dual-rotor system rub-impact test device according to claim 2, wherein the rub-impact body a (14), the rub-impact body B (15), the rub-impact body C (18) and the rub-impact body D (21) are all in a ring shape and are connected to the culvert casing (3) and the culvert casing (5), the rub-impact body a (14), the rub-impact body B (15), the rub-impact body C (18) and the rub-impact body D (21) are all provided with slopes, and when the rub-impact body is pressed in the axial direction by using a hydraulic device, the gap between the rotor blade and the culvert casing (3) or the culvert casing (5) is reduced.
4. The aircraft engine dual-rotor system rub-impact test device according to claim 1, wherein the side of the culvert casing (3) is provided with an opening and a local rub-impact device (23), the local rub-impact device (23) comprises a motor precession bolt (24), a fixing bolt (25), a rub-impact device main body (26) and a rub-impact ejector rod (27), the motor precession bolt (24) abuts against the rub-impact ejector rod (27) to move towards the inside of the culvert casing (3) through a stepping motor, so that the rotor-stator gap of the low-pressure compressor blade (4) is reduced, and the static gap reduction is equal to the rub-impact ejector rod movement amount.
5. The aircraft engine double-rotor system rub-impact test device according to claim 1, wherein a sealing labyrinth (20) is fixed at a turntable (22), the position of the sealing labyrinth along the axial direction is changed by increasing or decreasing gaskets between the sealing labyrinth (20) and the turntable (22), a sealing stator (19) at the position corresponding to the sealing labyrinth is a slope device, and the clearance between the sealing labyrinth and the sealing stator is reduced by increasing the gaskets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111170120.2A CN113899558B (en) | 2021-10-08 | 2021-10-08 | Friction test device for double-rotor system of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111170120.2A CN113899558B (en) | 2021-10-08 | 2021-10-08 | Friction test device for double-rotor system of aero-engine |
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| CN113899558A true CN113899558A (en) | 2022-01-07 |
| CN113899558B CN113899558B (en) | 2024-05-03 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113931872A (en) * | 2021-12-15 | 2022-01-14 | 成都中科翼能科技有限公司 | Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine |
| CN114575930A (en) * | 2022-05-06 | 2022-06-03 | 中国航发沈阳发动机研究所 | Supporting structure for intermediate fulcrum outer ring of engine |
| CN114858443A (en) * | 2022-03-22 | 2022-08-05 | 西北工业大学 | Small-sized double-rotor fault simulation experiment table and fault diagnosis simulation method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113931872A (en) * | 2021-12-15 | 2022-01-14 | 成都中科翼能科技有限公司 | Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine |
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| CN114858443A (en) * | 2022-03-22 | 2022-08-05 | 西北工业大学 | Small-sized double-rotor fault simulation experiment table and fault diagnosis simulation method |
| CN114575930A (en) * | 2022-05-06 | 2022-06-03 | 中国航发沈阳发动机研究所 | Supporting structure for intermediate fulcrum outer ring of engine |
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| Publication number | Publication date |
|---|---|
| CN113899558B (en) | 2024-05-03 |
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