CN113899558B - Friction test device for double-rotor system of aero-engine - Google Patents
Friction test device for double-rotor system of aero-engine Download PDFInfo
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- CN113899558B CN113899558B CN202111170120.2A CN202111170120A CN113899558B CN 113899558 B CN113899558 B CN 113899558B CN 202111170120 A CN202111170120 A CN 202111170120A CN 113899558 B CN113899558 B CN 113899558B
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- 238000012360 testing method Methods 0.000 title claims abstract description 9
- 230000003068 static effect Effects 0.000 claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 238000007789 sealing Methods 0.000 claims description 37
- 244000126211 Hericium coralloides Species 0.000 claims description 6
- 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
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
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- 238000011161 development Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000012544 monitoring process Methods 0.000 description 1
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- 238000012545 processing Methods 0.000 description 1
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Classifications
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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
-
- 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
-
- 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
-
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a friction test device for a double-rotor system of an aeroengine, 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 coupler, a high-pressure rotor coupler, a transmission gear box, an inner culvert casing and an outer culvert casing. The invention has the main structural components of the aero-engine, and corresponding measuring points can be arranged on the high-low pressure rotor and the casing, so that the unbalanced response, the intermediate bearing fault characteristic and the aero-engine rotating, static and rubbing fault characteristic of the double-rotor system of the aero-engine can be measured. The friction body with the slope is clamped on the casing, and the friction body is pressed in through a hydraulic device to adjust the static clearance of rotation, so that the dynamic characteristics of the aeroengine under the condition that the blades of the double-rotor wheel disc of the aeroengine and the stator are in full-circle friction are simulated.
Description
Technical Field
The invention belongs to the field of mechanical tests, and particularly relates to a collision and friction test device for a double-rotor system of an aero-engine.
Background
Aeroengines are a source of power for aircraft, and their reliability directly affects 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, an aeroengine mostly adopts a double-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 aero-engine is provided with blades on the double rotors, and the double rotors are supported on the casing, so that the blades of the double rotors can rub against the stator casing in the running process of the aero-engine. However, the aero-engine has a complex structure and a large number of vibration sources, which brings about corresponding difficulties for fault monitoring of the aero-engine. Therefore, the working mechanism of the avionic engine is clear, the operation state of key parts is monitored, and the method is very important for fault diagnosis of the avionic engine.
The prior art considers that the rubbing body is clamped on the casing, the rubbing fault of the fixed material under the fixed rotating and static gap can be only measured, the local rubbing condition can be simulated, and meanwhile, the rubbing body is more troublesome to replace.
Disclosure of Invention
The invention aims to solve the technical problems and further provides a collision and friction test device for a double-rotor system of an aero-engine.
The invention relates to a collision and friction test device of a double-rotor system of an aeroengine, 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 coupler 1, a high-pressure rotor coupler 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 the low-pressure rotor coupler 1, the high-pressure rotor 17 is connected with the low-pressure rotor 16 through the intermediate bearing 13, and can be connected with the motor through the high-pressure rotor coupler 8 and the transmission gear box 9; the low-pressure rotor 16 is supported on the outer culvert casing 3 through the low-pressure compressor support 2, the high-pressure rotor 17 is supported on the inner culvert casing 5 through the high-pressure compressor support 6 and the high-pressure turbine support 10, and the outer culvert casing 3 is supported on a rigid base;
The low-pressure rotor 16 comprises a rotating shaft and two turntables, the two turntables are respectively connected with the low-pressure compressor blade 4 and the low-pressure turbine blade 12 through bolts, the turntables are provided with sealing comb teeth 20, and the sealing comb teeth 20 adjust the overhanging amount through bolts and gaskets; the high-pressure rotor 17 comprises a rotating shaft and two turntables, the two turntables are respectively connected with the high-pressure compressor blade 7 and the high-pressure turbine blade 11 through bolts, and sealing comb teeth 20 are arranged on the turntables.
Further, the connotation casing 5 is axially embedded with the rubbing body B15 and the rubbing body C18, and the positions are adjusted through the axial embedding amount, so that the rubbing gap is controlled; the external culvert casing 3 is embedded with a rubbing body A14 and a rubbing body D21, and the positions are adjusted by the axial embedding amount so as to control the rubbing clearance; the local rubbing device 23 is arranged on the outer culvert casing 3 and is connected with a rubbing device main body 26 through a fixing bolt 25, a motor screwing bolt 24 is arranged in the rubbing device main body 26, and the screwing or unscrewing of the motor screwing bolt 24 is controlled through an external stepping motor, so that the feeding amount of a rubbing ejector rod 27 is controlled.
Further, the rubbing body a14, the rubbing body B15, the rubbing body C18 and the rubbing body D21 are all annular and connected to the outer culvert casing 3 and the inner culvert casing 5, and slopes are formed on the rubbing body a14, the rubbing body B15, the rubbing body C18 and the rubbing body D21, so that when the rubbing body is pressed in the axial direction by using a hydraulic device, the gap between the rotor blade and the outer culvert casing 3 or the inner culvert casing 5 is reduced.
Further, the side surface of the outer culvert casing 3 is provided with an opening and a local rubbing device 23, the local rubbing device 23 comprises a motor screwing bolt 24, a fixing bolt 25, a rubbing device main body 26 and a rubbing mandril 27, and the motor screwing bolt 24 is propped against the rubbing mandril 27 to move into the outer culvert casing 3 through a stepping motor, so that the rotating static clearance of the low-pressure compressor blade 4 is reduced, and the rotating static clearance reduction is equal to the rubbing mandril moving amount.
Further, a sealing comb 20 is fixed at the rotary table 22, the axial position of the sealing comb is changed by increasing or decreasing the gasket between the sealing comb 20 and the rotary table 22, a sealing stator 19 at the corresponding position of the sealing comb is a slope device, and the gap between the sealing comb and the sealing stator is reduced by increasing the gasket.
Advantageous effects
The device has a structure similar to that of a real aeroengine, particularly the intermediate bearing and the casing, so that the dynamic characteristics of the aeroengine can be reflected, meanwhile, the device is provided with various friction parts, the friction between the double-rotor wheel disc blade and the casing and the friction between the sealing comb disc and the casing can be carried out, the device can simulate the situation of friction all around except the local point friction simulation, meanwhile, the friction body is convenient to replace, and the static clearance is adjustable. The dynamic characteristics of the aero-engine under various rub-impact faults can be reflected. The whole structure is scientific, the processing is easy, the disassembly and the assembly are convenient, and the popularization and the promotion are easy.
The invention maintains the main structural components of the aero-engine, in particular the intermediate bearing and the casing, thereby reflecting the dynamics of the real aero-engine. Corresponding measuring points can be arranged on the high-low pressure rotor and the casing, so that unbalanced response, intermediate bearing fault characteristics and aeroengine rotating, static and rubbing fault characteristics of the double-rotor system of the aeroengine can be measured. The friction body with the slope is clamped on the casing, and the friction body is pressed in through a hydraulic device to adjust the static clearance of rotation, so that the dynamic characteristics of the aeroengine under the condition that the blades of the double-rotor wheel disc of the aeroengine and the stator are in full-circle friction are simulated.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of the position of the localized rubbing device of the present invention;
Fig. 3 is a schematic structural view of a partial rubbing device according to the present invention.
The reference numerals are as follows:
The device comprises a low-pressure rotor coupler 1, a low-pressure compressor support 2, an outer culvert casing 3, a low-pressure compressor blade 4, an inner culvert casing 5, a high-pressure compressor support 6, a high-pressure compressor blade 7, a high-pressure rotor coupler 8, a transmission gear box 9, a high-pressure turbine support 10, a high-pressure turbine blade 11, a low-pressure turbine blade 12, a medium bearing 13, a friction body A14, a friction body B15, a low-pressure rotor 16, a high-pressure rotor 17, a friction body C18, a sealing stator 19, a sealing comb tooth 20, a friction body D21, a rotary disc 22, a local friction device 23, a motor screwing bolt 24, a fixed bolt 25, a friction device body 26 and a friction ejector rod 27.
Detailed Description
The present embodiment will be specifically described with reference to fig. 1 to 3.
The invention relates to a friction test device for a double-rotor system of an aero-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 coupler 1, a high-pressure rotor coupler 8, a transmission gear box 9, an inner culvert casing 5 and an outer culvert casing 3. The low-pressure rotor 16 is connected to the motor via the low-pressure rotor coupling 1, the high-pressure rotor 17 is connected to the low-pressure rotor 16 via the intermediate bearing 13, and can be connected to the motor via the high-pressure rotor coupling 8 and the transmission gearbox 9. The low-pressure rotor 16 is supported by the outer casing 3 via the low-pressure compressor bearing 2, the high-pressure rotor 17 is supported by the inner casing 5 via the high-pressure compressor bearing 6 and the high-pressure turbine bearing 10, and the outer casing 3 is supported on a rigid base.
The low-pressure rotor 16 comprises a rotating shaft and two turntables, the two turntables are respectively connected with the low-pressure compressor blade 4 and the low-pressure turbine blade 12 through bolts, sealing comb teeth 20 are arranged on the turntables, and the extending amount of the sealing comb teeth 20 is adjusted through bolts and gaskets; the high-pressure rotor 17 comprises a rotating shaft and two turntables, the two turntables are respectively connected with the high-pressure compressor blade 7 and the high-pressure turbine blade 11 through bolts, and sealing comb teeth 20 are arranged on the turntables. The connotation casing 5 is axially embedded with the rubbing body B15 and the rubbing body C18, and the positions are adjusted through the axial embedding amount, so that the rubbing clearance is controlled; the external culvert casing 3 is embedded with a rubbing body A14 and a rubbing body D21, and the positions are adjusted by the axial embedding amount so as to control the rubbing clearance; the local rubbing device 23 is arranged on the outer culvert casing 3 and is connected with the rubbing device main body 26 through a fixing bolt 25, a motor screwing bolt 24 is arranged in the rubbing device main body 26, and the motor screwing bolt 24 is controlled to screw in or screw out through an external stepping motor, so that the feeding amount of the rubbing push rod 27 is influenced, and the rubbing gap is controlled. The friction body A14, the friction body B15, the friction body C18 and the friction body D21 are annular and are connected to the outer culvert casing 3 and the inner culvert casing 5, slopes are arranged on the friction body A14, the friction body B15, the friction body C18 and the friction body D21, when the friction bodies are pressed in along the axial direction by using a hydraulic device, the gap between the rotor blade and the outer culvert casing 3 or the inner culvert casing 5 is reduced, and the reduced gap amount is related to the axial pressed-in distance, so that a rotating and static gap is determined.
The outer culvert casing 3 side is equipped with trompil and local device 23 that rubs, and the local device 23 that rubs includes motor precession bolt 24, fixing bolt 25, rubs device main part 26 and rubs ejector pin 27, makes motor precession bolt 24 jack rub ejector pin 27 to advance in outer culvert casing 3 through step motor to make the quiet clearance of changeing of low pressure compressor blade 4 reduce, changeing quiet clearance reduction and be equal to rub ejector pin volume of marcing. The sealing comb teeth 20 are fixed at the rotary table 22, the axial positions of the sealing comb teeth are changed by increasing and decreasing gaskets between the sealing comb teeth 20 and the rotary table 22, the sealing stators 19 at the positions corresponding to the sealing comb teeth are slope devices, and gaps between the sealing comb teeth and the sealing stators are reduced by increasing the gaskets.
Installation instruction
The low pressure rotor 16 has a shaft and two turntables, wherein the two turntables are respectively connected with the low pressure compressor blade 4 and the low pressure turbine blade 12 by bolts, each turntable is provided with a sealing comb 20, and the sealing comb 20 can adjust the overhanging amount by bolts and gaskets. The high-pressure rotor 17 likewise has a rotary shaft and two rotary disks, wherein the two rotary disks are also connected to the high-pressure compressor blade 7 and the high-pressure turbine blade 11 by bolts, respectively, and each rotary disk is also provided with sealing comb teeth 20. The low-pressure rotor 16 is connected to the motor via the low-pressure rotor coupling 1, the high-pressure rotor 17 is connected to the low-pressure rotor 16 via the intermediate bearing 13, and can be connected to the motor via the high-pressure rotor coupling 8 and the transmission gearbox 9. The low-pressure rotor 16 is supported by the low-pressure compressor support 2 on the outer casing 3, and the high-pressure rotor 17 is supported by the high-pressure compressor support 6 and the high-pressure turbine support 10 on the inner casing 5.
The friction body B15 and the friction body C18 can be axially embedded in the inner container casing 5, and the position can be adjusted by the axial embedding amount so as to control the friction clearance. The friction body A14 and the friction body D21 can be embedded in the outer culvert casing 3, and the position can be adjusted by the axial embedding amount so as to control the friction clearance.
The local rubbing device 23 is located on the outer culvert casing 3, is connected with the rubbing device main body 26 through a fixing bolt 25, and a motor screwing bolt 24 is arranged in the rubbing device main body 26, and can be controlled to screw in or screw out through an external stepping motor, so that the feeding amount of the rubbing push rod 27 is influenced, and the rubbing gap is controlled.
The foregoing is merely illustrative of the preferred embodiments of the present invention and is not intended to limit the embodiments of the present invention, and those skilled in the art can easily make corresponding variations or modifications according to the main concept and spirit of the present invention, so the protection scope of the present invention shall be defined by the claims.
Claims (2)
1. The device 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 coupler (1), a high-pressure rotor coupler (8), a transmission gearbox (9), an inner box (5), an outer box (3), a low-pressure compressor blade (4), a low-pressure turbine blade (12), a sealing comb (20), a high-pressure compressor blade (7), a high-pressure turbine blade (11), a rubbing body A (14), a rubbing body B (15), a rubbing body C (18), a rubbing body D (21), a local rubbing device (23), a motor screwing bolt (24) and a rubbing ejector rod (27);
The low-pressure rotor (16) is connected with the motor through a low-pressure rotor coupler (1), the high-pressure rotor (17) is connected with the low-pressure rotor (16) through an intermediate bearing (13), and the high-pressure rotor coupler (8) and the transmission gear box (9) can be connected with the motor; the low-pressure rotor (16) is supported on the outer culvert casing (3) through the low-pressure compressor support (2), the high-pressure rotor (17) is supported on the inner culvert casing (5) through the high-pressure compressor support (6) and the high-pressure turbine support (10), and the outer culvert casing (3) is supported on the rigid base;
The low-pressure rotor (16) comprises a rotating shaft and two turntables, the two turntables are respectively connected with the low-pressure compressor blades (4) and the low-pressure turbine blades (12) through bolts, sealing comb teeth (20) are arranged on the turntables, and the extending amount of the sealing comb teeth (20) is adjusted through bolts and gaskets; the high-pressure rotor (17) comprises a rotating shaft and two turntables, the two turntables are respectively connected with the high-pressure compressor blades (7) and the high-pressure turbine blades (11) through bolts, and sealing comb teeth (20) are arranged on the turntables;
the inner box (5) is axially embedded with the rubbing body B (15) and the rubbing body C (18), and the positions are adjusted through the axial embedding amount, so that the rubbing gap is controlled; the friction body A (14) and the friction body D (21) are embedded in the outer culvert casing (3), and the positions are adjusted through the axial embedding amount so as to control the friction clearance; the local friction device (23) is arranged on the culvert casing (3) and is connected with the friction device main body (26) through a fixing bolt (25), a motor screwing bolt (24) is arranged in the friction device main body (26), and the motor screwing bolt (24) is controlled to screw in or screw out through an external stepping motor, so that the feeding amount of the friction ejector rod (27) is controlled;
The side surface of the outer culvert casing (3) is provided with an opening and a local rubbing device (23), the local rubbing device (23) comprises a motor screwing bolt (24), a fixing bolt (25), a rubbing device main body (26) and a rubbing ejector rod (27), the motor screwing bolt (24) is propped against the rubbing ejector rod (27) to move into the outer culvert casing (3) through a stepping motor, so that the rotating static clearance of the low-pressure compressor blade (4) is reduced, and the rotating static clearance reduction is equal to the moving quantity of the rubbing ejector rod (27);
the friction body A (14), the friction body B (15), the friction body C (18) and the friction body D (21) are annular and are connected to the outer culvert casing (3) and the inner culvert casing (5), slopes are arranged on the friction body A (14), the friction body B (15), the friction body C (18) and the friction body D (21), and when the friction body is pressed in along the axial direction by using a hydraulic device, gaps between the rotor blades and the outer culvert casing (3) or the inner culvert casing (5) are reduced.
2. The aeroengine double-rotor system friction test device according to claim 1, wherein a sealing comb tooth (20) is fixed at a rotary table (22), the axial position of the sealing comb tooth is changed by increasing and decreasing gaskets between the sealing comb tooth (20) and the rotary table (22), a sealing stator (19) at the corresponding position of the sealing comb tooth is a slope device, and the gaps between the sealing comb tooth and the sealing stator are 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 CN113899558A (en) | 2022-01-07 |
| CN113899558B true CN113899558B (en) | 2024-05-03 |
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| CN202111170120.2A Active CN113899558B (en) | 2021-10-08 | 2021-10-08 | Friction test device for double-rotor system of aero-engine |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113931872B (en) * | 2021-12-15 | 2022-03-18 | 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 |
| CN114858443B (en) * | 2022-03-22 | 2023-06-27 | 西北工业大学 | Small-sized double-rotor fault simulation experiment table and fault diagnosis simulation method |
| CN114575930B (en) * | 2022-05-06 | 2022-08-19 | 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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