CN103586827A - Axial-flow compressor unit body component assembling device and method - Google Patents
Axial-flow compressor unit body component assembling device and method Download PDFInfo
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- CN103586827A CN103586827A CN201310563966.1A CN201310563966A CN103586827A CN 103586827 A CN103586827 A CN 103586827A CN 201310563966 A CN201310563966 A CN 201310563966A CN 103586827 A CN103586827 A CN 103586827A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
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Abstract
The invention relates to an axial-flow compressor unit body component assembling device and method. According to the technical scheme, the axial-flow compressor unit body component assembling device comprises a base and a centering mechanism, wherein the base comprises a disc, supporting legs, a first positioning semiring, a second positioning semiring and a positioning sleeve, the supporting legs are arranged below the disc, and the first positioning semiring, the second positioning semiring and the positioning sleeve are arranged on the disc; the centering mechanism comprises a hollow shaft and a positioning cover, the hollow shaft is arranged in the center of the positioning cover, and the outer edge of the positioning cover is provided with a positioning edge. According to the technical scheme, conformity between axial clearance and radial clearance between a rotor and a stator of an axial-flow compressor and technical requirements can be check in advance, the axial-flow compressor is installed on an aircraft engine in the mode of an axial-flow compressor unit body component, the number of times for repeated assembly is reduced, and the assembly period of the aircraft engine is shortened.
Description
Technical field
The present invention relates to a kind of assembling device and assembly method, particularly relate to a kind of axial-flow compressor cell cube assembly mounting device and assembly method thereof.
Background technology
Aero-engine is when carrying out final assembly, need to check the gap of rotor and the stator of axial-flow compressor, generally, to check after the rotor of axial-flow compressor, stator are installed on engine, when finding that the gap of rotor and stator does not meet specification requirement, also need the rotor of axial-flow compressor, stator to unload and decompose troubleshooting, affect the assembly period of engine.
Particularly, for a kind of axial-flow compressor, its opposite opened stator casing is inner stopper location and interference fit, cannot in aero-engine, directly install.
Summary of the invention
The invention provides a kind of axial-flow compressor cell cube assembly mounting device and assembly method thereof, can check in advance the end play of axial-flow compressor rotor and stator and the compatibility of radial clearance and specification requirement, with axial-flow compressor cell cube kit form, be installed in aero-engine, reduce and to repeat to assemble number of times and aero-engine assembly period.
Technical scheme of the present invention is as follows:
A kind of axial-flow compressor cell cube assembly mounting device, comprise base and centering machine, described base comprises disk, leg, location semi-ring one, location semi-ring two and positioning sleeve, described leg is arranged on below described disk, and described location semi-ring one, location semi-ring two and positioning sleeve are arranged on above described disk; Described centering machine comprises hollow shaft and locating cover, and described hollow shaft is arranged on described locating cover center, and the outer rim of described locating cover arranges gulde edge.
Described axial-flow compressor cell cube assembly mounting device preferred version is: between described location semi-ring one and location semi-ring two and described disk, alignment pin is set.
Above-mentioned axial-flow compressor cell cube assembly mounting device can also arrange locating shaft between described positioning sleeve and described disk, for the relative position between fixing described positioning sleeve and described disk.
The present invention also provides a kind of axial-flow compressor cell cube component assembling method, described axial-flow compressor cell cube assembly comprises rotor and stator, in described rotor, be provided with internal point, described stator comprises first casing and second casing, described method is utilized above-mentioned axial-flow compressor cell cube assembly mounting device, and described method comprises the steps:
(1) described base is put on platform, adjust described leg and make the upper surface of described location semi-ring one and location semi-ring two in level, described location semi-ring one and location semi-ring two are used for simulating the position of the fulcrum of described stator under described axial-flow compressor cell cube component assembling state;
(2) described positioning sleeve is used for simulating the position of the fulcrum of described rotor under described axial-flow compressor cell cube component assembling state, to guarantee the relative position of described rotor and described stator, described rotor is arranged on described positioning sleeve;
(3) open described location semi-ring one and location semi-ring two, described first casing and second casing are arranged on described location semi-ring one and location semi-ring two, load onto for being fixedly connected with the counterpart screw bolt and nut of described first casing and second casing; Install described centering machine, described hollow shaft is inserted to described internal point, described gulde edge is connected with bolt with second casing with described first casing;
(4) with bolt, second casing is fixedly connected on described location semi-ring two, separately counterpart screw bolt and nut, unloads the bolt that connects described gulde edge and described first casing, and described first casing is removed;
(5) measure end play and the radial clearance of described stator and described rotor;
(6) measurement result does not meet specification requirement, unloads described rotor and stator and reprocesses;
(7) measurement result meets specification requirement, described first casing is installed on described location semi-ring one, install for being fixedly connected with the counterpart screw bolt and nut of described first casing and second casing, install the bolt that connects described gulde edge and described first casing, separately connect the bolt between described first casing and location semi-ring one and between second casing and location semi-ring two, utilize suspender that described axial-flow compressor cell cube assembly is installed in aero-engine.
Beneficial effect of the present invention:
1, the axial-flow compressor cell cube assembly mounting device described in the present invention can be simulated the confined state of axial-flow compressor in aero-engine; Utilize described axial-flow compressor cell cube assembly mounting device, can check in advance that axial-flow compressor turns, the end play between stator and the compatibility of radial clearance and specification requirement, discovery does not in advance meet the parts of specification requirement.Minimizing because engine axial-flow compressor turns, stator gap do not meet repeating that specification requirement causes and assembles number of times and engine assembly cycle.
2, technical scheme of the present invention, can realize axial-flow compressor and be installed in aero-engine with cell cube kit form, has improved production efficiency, has reduced labor strength.
3, technical scheme of the present invention, opposite opened stator casing and its rotor that can to realize positioning form be inner stopper and interference fit are mounted for axial-flow compressor cell cube assembly.
4, between described location semi-ring one and location semi-ring two and described disk, alignment pin is set, can carries out angle location to described first casing and second casing, to guarantee that the position of described first casing and second casing meets specification requirement.
Accompanying drawing explanation
Fig. 1 is understructure schematic diagram;
Fig. 2 is centering machine structural representation cutaway view;
Fig. 3 is axial-flow compressor cell cube component assembling view;
In figure: 1 is disk, 2 is leg, and 3 for location semi-ring one, 4 is positioning sleeve for locating semi-ring two, 5, and 6 is locating cover, and 7 is hollow shaft, and 8 is gulde edge, and 9 is second casing, and 10 is first casing, and 11 is rotor.
The specific embodiment
As shown in Figure 1, 2, a kind of axial-flow compressor cell cube assembly mounting device, comprise base and centering machine, described base comprises disk 1, leg 2, location semi-ring 1, location semi-ring 24 and positioning sleeve 5, described leg 2 is arranged on below described disk 1, and described location semi-ring 1, location semi-ring 24 and positioning sleeve 5 are arranged on above described disk 1; Described centering machine comprises hollow shaft 7 and locating cover 6, and described hollow shaft 7 is arranged on described locating cover 6 centers, and the outer rim of described locating cover 6 arranges gulde edge 8.Between described location semi-ring 1 and location semi-ring 24 and described disk 1, alignment pin is set.Between described positioning sleeve 5 and described disk 1, locating shaft is set, for the relative position between fixing described positioning sleeve 5 and described disk 1.
As shown in Figure 3, the present invention also provides a kind of axial-flow compressor cell cube component assembling method, described axial-flow compressor cell cube assembly comprises rotor 11 and stator, in described rotor 11, be provided with internal point, described stator comprises first casing 10 and second casing 9, described method is utilized above-mentioned axial-flow compressor cell cube assembly mounting device, and described method comprises the steps:
(1) described base is put on platform, adjust described leg 2 and make the upper surface of described location semi-ring 1 and location semi-ring 24 in level, described location semi-ring 1 and location semi-ring 24 are used for simulating the position of the fulcrum of described stator under described axial-flow compressor cell cube component assembling state;
(2) described positioning sleeve 5 is used for simulating the position of the fulcrum of described rotor under described axial-flow compressor cell cube component assembling state, to guarantee the relative position of described rotor 11 and described stator, described rotor 11 is arranged on described positioning sleeve 5;
(3) open described location semi-ring 1 and location semi-ring 24, described first casing 10 and second casing 9 are arranged on described location semi-ring 1 and location semi-ring 24, load onto for being fixedly connected with the counterpart screw bolt and nut of described first casing 10 and second casing 9; Install described centering machine, described hollow shaft 7 is inserted to described internal point, described gulde edge 8 is connected with bolt with second casing 9 with described first casing 10;
(4) with bolt, second casing 9 is fixedly connected on described location semi-ring 24, separately counterpart screw bolt and nut, unloads the bolt that connects described gulde edge 8 and described first casing 10, and described first casing 10 is removed;
(5) measure end play and the radial clearance of described stator and described rotor 11;
(6) measurement result does not meet specification requirement, unloads described rotor 11 and stator and reprocesses;
(7) measurement result meets specification requirement, described first casing 10 is installed on described location semi-ring 1, install for being fixedly connected with the counterpart screw bolt and nut of described first casing 10 and second casing 9, install the bolt that connects described gulde edge 8 and described first casing 10, separately connect the bolt between described first casing 10 and location semi-ring 1 and between second casing 9 and location semi-ring 24, utilize suspender that described axial-flow compressor cell cube assembly is installed in aero-engine.
Claims (4)
1. an axial-flow compressor cell cube assembly mounting device, it is characterized in that, described device comprises base and centering machine, described base comprises disk, leg, location semi-ring one, location semi-ring two and positioning sleeve, described leg is arranged on below described disk, and described location semi-ring one, location semi-ring two and positioning sleeve are arranged on above described disk; Described centering machine comprises hollow shaft and locating cover, and described hollow shaft is arranged on described locating cover center, and the outer rim of described locating cover arranges gulde edge.
2. axial-flow compressor cell cube assembly mounting device according to claim 1, is characterized in that, between described location semi-ring one and location semi-ring two and described disk, alignment pin is set.
3. axial-flow compressor cell cube assembly mounting device according to claim 1 and 2, is characterized in that, between described positioning sleeve and described disk, locating shaft is set, for the relative position between fixing described positioning sleeve and described disk.
4. an axial-flow compressor cell cube component assembling method, it is characterized in that, described axial-flow compressor cell cube assembly comprises rotor and stator, in described rotor, be provided with internal point, described stator comprises first casing and second casing, the axial-flow compressor cell cube assembly mounting device of described method utilization as described in claim 1～3, described method comprises the steps:
(1) described base is put on platform, adjust described leg and make the upper surface of described location semi-ring one and location semi-ring two in level, described location semi-ring one and location semi-ring two are used for simulating the position of the fulcrum of described stator under described axial-flow compressor cell cube component assembling state;
(2) described positioning sleeve is used for simulating the position of the fulcrum of described rotor under described axial-flow compressor cell cube component assembling state, to guarantee the relative position of described rotor and described stator, described rotor is arranged on described positioning sleeve;
(3) open described location semi-ring one and location semi-ring two, described first casing and second casing are arranged on described location semi-ring one and location semi-ring two, load onto for being fixedly connected with the counterpart screw bolt and nut of described first casing and second casing; Install described centering machine, described hollow shaft is inserted to described internal point, described gulde edge is connected with bolt with second casing with described first casing;
(4) with bolt, second casing is fixedly connected on described location semi-ring two, separately counterpart screw bolt and nut, unloads the bolt that connects described gulde edge and described first casing, and described first casing is removed;
(5) measure end play and the radial clearance of described stator and described rotor;
(6) measurement result does not meet specification requirement, unloads described rotor and stator and reprocesses;
(7) measurement result meets specification requirement, described first casing is installed on described location semi-ring one, install for being fixedly connected with the counterpart screw bolt and nut of described first casing and second casing, install the bolt that connects described gulde edge and described first casing, separately connect the bolt between described first casing and location semi-ring one and between second casing and location semi-ring two, utilize suspender that described axial-flow compressor cell cube assembly is installed in aero-engine.
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| CN201310563966.1A CN103586827B (en) | 2013-11-11 | 2013-11-11 | Axial-flow compressor unit body component assembling device and method |
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| CN201310563966.1A CN103586827B (en) | 2013-11-11 | 2013-11-11 | Axial-flow compressor unit body component assembling device and method |
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| CN104440761A (en) * | 2014-09-29 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor dual ring press assembling device and method |
| CN104454660A (en) * | 2014-11-07 | 2015-03-25 | 中航工业贵州航空动力有限公司 | Assembly method for half rings of aero-engine compressor casing |
| CN105458647A (en) * | 2015-11-20 | 2016-04-06 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembling method for power turbine without adjustment of axial gap between rotor and stator |
| CN106640770A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Assembly method of low-pressure supercharging device used for bi-rotor gas turbine |
| CN107263042A (en) * | 2016-04-08 | 2017-10-20 | 贵州黎阳航空动力有限公司 | Aero-engine high-pressure compressor assembles centering and rotating device |
| CN108362501A (en) * | 2017-12-27 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of rack installation method for aviation axial flow compressor performance test |
| CN109514465A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of long axis class spare part assembly guide clamp and application method |
| CN110328493A (en) * | 2019-06-28 | 2019-10-15 | 中国航发南方工业有限公司 | The method for controlling the axial gap between the blade tip and outer cover of centrifugal impeller |
| CN111376192A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Be used for compressor stator subassembly assembly combination processingequipment |
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| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
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| CN104440761A (en) * | 2014-09-29 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor dual ring press assembling device and method |
| CN104440761B (en) * | 2014-09-29 | 2016-04-27 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rotor dicyclo compression fit Apparatus and method for |
| CN104454660A (en) * | 2014-11-07 | 2015-03-25 | 中航工业贵州航空动力有限公司 | Assembly method for half rings of aero-engine compressor casing |
| CN105458647A (en) * | 2015-11-20 | 2016-04-06 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembling method for power turbine without adjustment of axial gap between rotor and stator |
| CN107263042B (en) * | 2016-04-08 | 2023-11-21 | 中国航发贵州黎阳航空动力有限公司 | Centering rotating device for assembling high-pressure compressor of aero-engine |
| CN107263042A (en) * | 2016-04-08 | 2017-10-20 | 贵州黎阳航空动力有限公司 | Aero-engine high-pressure compressor assembles centering and rotating device |
| CN106640770B (en) * | 2016-12-23 | 2019-05-14 | 贵州黎阳航空动力有限公司 | A kind of birotor combustion engine low-pressure supercharging device assembly method |
| CN106640770A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Assembly method of low-pressure supercharging device used for bi-rotor gas turbine |
| CN108362501A (en) * | 2017-12-27 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of rack installation method for aviation axial flow compressor performance test |
| CN109514465A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of long axis class spare part assembly guide clamp and application method |
| CN110328493A (en) * | 2019-06-28 | 2019-10-15 | 中国航发南方工业有限公司 | The method for controlling the axial gap between the blade tip and outer cover of centrifugal impeller |
| CN110328493B (en) * | 2019-06-28 | 2020-07-24 | 中国航发南方工业有限公司 | Method for controlling the axial clearance between the tip of a centrifugal impeller and a shroud |
| CN111376192A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Be used for compressor stator subassembly assembly combination processingequipment |
| CN111376192B (en) * | 2020-03-31 | 2022-02-11 | 中国航发动力股份有限公司 | Be used for compressor stator subassembly assembly combination processingequipment |
| CN112113480A (en) * | 2020-09-18 | 2020-12-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Auxiliary tool and method for measuring assembly clearance of fan unit body |
| CN113914999A (en) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | Gas turbine compressor assembling method |
| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
| CN115431013A (en) * | 2022-08-15 | 2022-12-06 | 北京动力机械研究所 | Turbofan engine case press-mounting device |
| CN115431013B (en) * | 2022-08-15 | 2024-04-09 | 北京动力机械研究所 | Turbofan engine casing press-fitting device |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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