CN106677907A - Aero-engine high-pressure rotor electric rocking-turning tool - Google Patents
Aero-engine high-pressure rotor electric rocking-turning tool Download PDFInfo
- Publication number
- CN106677907A CN106677907A CN201611046654.3A CN201611046654A CN106677907A CN 106677907 A CN106677907 A CN 106677907A CN 201611046654 A CN201611046654 A CN 201611046654A CN 106677907 A CN106677907 A CN 106677907A
- Authority
- CN
- China
- Prior art keywords
- engine high
- pressure rotor
- engine
- rocking
- controller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
Abstract
The invention discloses an aero-engine high-pressure rotor electric rocking-turning tool. The aero-engine high-pressure rotor electric rocking-turning tool comprises a host unit and a control unit; the host unit consists of an engine interface accessory (1), a speed reducing device (2), a direct-current motor (3) and a motor brake (4); the control unit consists of an encoder (5), a controller (6) and a remote control device (7), wherein the host unit is connected with an engine high-pressure rotor rocking-turning base through the engine interface accessory (1); the aero-engine high-pressure rotor electric rocking-turning tool is steady in rotating speed; and the rotating speed is adjustable within 0 to 5 rpm through a controller at any time according to an actual requirement of examination of an engine high-pressure blade, and the operating is steady. When the engine high-pressure blade is examined, reverse rotation or pause can be realized through the controller when a problematic blade is required to be rotated back to examine in detail and when the blade is measured.
Description
Technical field
The present invention relates to the structure design and applied technical field of rocking-turn instrument, a kind of aero-engine is specifically provided high
Pressure rotor motor-driven rocking-turn instrument.
Background technology
Certain type aero-engine is larger in outfield usage amount, and on-wing maintenance, regular inspection inspection and work of lengthening the life etc. are needed
Engine runner is checked, workload is very heavy.At present, the rocking-turn mode of high pressure rotor uses manually rocking-turn, completes
, it is necessary to 2 people complete during the work such as runner inspection, wherein 1 people's rocking-turn, 1 people inspection, it is impossible to reach precise and stable turn of high pressure rotor
It is dynamic.
People are highly desirable to be obtained a kind of excellent aircraft engine high pressure rotor electric rocking of technique effect and changes a job tool.
The content of the invention
Changed a job tool it is an object of the invention to provide a kind of excellent aircraft engine high pressure rotor electric rocking of technique effect.With
In the high pressure rotor rocking-turns such as on-wing maintenance, regular inspection inspection and work of lengthening the life work, it is possible to achieve high pressure rotor accurately turns
It is dynamic, can accurate positive and negative rotation instrument, using Electronic control, reduce human cost, increase operating efficiency.
The aircraft engine high pressure rotor electric rocking changes a job to have includes main computer unit and control unit, the main computer unit
Constitute as follows：Engine interface annex 1, deceleration device 2, direct current generator 3 and motor stop 4, and control unit constitutes as follows：Encoder
5th, controller 6 and remote control 7；Wherein, the main computer unit is by engine interface annex 1 and engine high pressure rotor rocking-turn
Base is connected, and direct current generator 3 is connected by deceleration device 2, engine interface annex 1 with engine rotor, high-voltage electric rocking-turn
The main computer unit of device drives deceleration device 2 by direct current generator 3, then is installed to a whole set of frock by engine interface annex 1
On engine high pressure rotor rocking-turn base, motor is stopped and 4 is connected with direct current generator 3, and 4 realizations of stopping of DC. machine design motor were operated
Emergent stopping in journey.Encoder 5 is located at the rear end of direct current generator 3, and encoder is experienced high-voltage electric rocking-turn device rotary speed and is supplied to
Controller simultaneously shows.Encoder 5 is connected with controller 6, and controller 6 passes through control line or or remote control 7 and the phase of direct current generator 3
Even, the starting of dc source and controlled motor is provided for motor, is stopped, main story, reversion accelerates, and slows down.Control signal can also
By remote control device 7 at 20 meters apart from interior controlled in wireless.
Aircraft engine high pressure rotor electric rocking tool of changing a job can carry out accurate rocking-turn, realize that rotating speed is steady, can be with
Regulate the speed at any time as needed and direction, reduce human cost, increase operating efficiency, daily dimension is reduced in flight-line service work
The people of shield personnel 1, can reduce personnel's pressure of execution task, and separate unit engine high pressure compressor blade inspection can save for 4 man-hours, together
When due to electric rocking change a job tool rotating speed uniform, controllable, it is contemplated that lifting operating efficiency 20%.Using electric-powered replacement manual work,
Realize electronic, accurate high pressure rotor rocking-turn.
Aircraft engine high pressure rotor electric rocking tool rotating speed of changing a job is steady, can regulate the speed at any time as needed with
Direction；With wireless regulatory function；It is capable of achieving to carry the rocking-turn of powering of movable simple lithium battery power supply to be powered with ground power supply and shake
Turn；Can be actually needed according to engine high pressure blade inspection and realize at any time that rotor speed can in 0 to 5 revs/min by controller
Adjust, and smooth running.Carrying out finding that problematic blade needs revolution to check and measure in detail when engine high pressure blade is checked
When can by controller realize invert.
Brief description of the drawings
Below in conjunction with the accompanying drawings and implementation method the present invention is further detailed explanation：
Fig. 1 changes a job tool principle schematic for aircraft engine high pressure rotor electric rocking.
Specific embodiment
Embodiment 1
The aircraft engine high pressure rotor electric rocking changes a job to have includes main computer unit and control unit, the main computer unit
Constitute as follows：Engine interface annex 1, deceleration device 2, direct current generator 3 and motor stop 4, and control unit constitutes as follows：Encoder
5th, controller 6 and with remote control 7；Wherein, the main computer unit is shaken by engine interface annex 1 with engine high pressure rotor
Turn base to be connected, direct current generator 3 is connected by deceleration device 2, engine interface annex 1 with engine rotor, and high-tension electricity shakes
The main computer unit of rotary device drives deceleration device 2 by direct current generator 3, then is installed a whole set of frock by engine interface annex 1
Onto engine high pressure rotor rocking-turn base, motor is stopped and 4 is connected with direct current generator 3, and DC. machine design motor is stopped 4 realizations operating
During emergent stopping.Encoder 5 is located at the rear end of direct current generator 3, and encoder experiences the offer of high-voltage electric rocking-turn device rotary speed
To controller and show.Encoder 5 is connected with controller 6, and controller 6 is by control line or or remote control 7 and direct current generator 3
It is connected, the starting of dc source and controlled motor is provided for motor, stop, main story, reversion accelerates, and slows down.Control signal also may be used
With by remote control device 7 at 20 meters apart from interior controlled in wireless.
Aircraft engine high pressure rotor electric rocking tool of changing a job can carry out accurate rocking-turn, realize that rotating speed is steady, can be with
Regulate the speed at any time as needed and direction, reduce human cost, increase operating efficiency, daily dimension is reduced in flight-line service work
The people of shield personnel 1, can reduce personnel's pressure of execution task, and separate unit engine high pressure compressor blade inspection can save for 4 man-hours, together
When due to electric rocking change a job tool rotating speed uniform, controllable, it is contemplated that lifting operating efficiency 20%.Using electric-powered replacement manual work,
Realize electronic, accurate high pressure rotor rocking-turn.
Aircraft engine high pressure rotor electric rocking tool rotating speed of changing a job is steady, can regulate the speed at any time as needed with
Direction；With wireless regulatory function；It is capable of achieving to carry the rocking-turn of powering of movable simple lithium battery power supply to be powered with ground power supply and shake
Turn；Can be actually needed according to engine high pressure blade inspection and realize at any time that rotor speed can in 0 to 5 revs/min by controller
Adjust, and smooth running.Carrying out finding that problematic blade needs revolution to check and measure in detail when engine high pressure blade is checked
When can by controller realize invert.
Claims (1)
1. a kind of aircraft engine high pressure rotor electric rocking is changed a job tool, it is characterised in that：The aircraft engine high pressure rotor electricity
Shaking tool of changing a job includes main computer unit and control unit, and the main computer unit constitutes as follows：Engine interface annex (1), deceleration
Device (2), direct current generator (3) and motor are stopped (4), and control unit constitutes as follows：Encoder (5), controller (6) and remote control
(7)；Wherein, the main computer unit is connected by engine interface annex (1) with engine high pressure rotor rocking-turn base, direct current
Machine (3) is connected by deceleration device (2) and engine interface annex (1) with engine rotor driver, and motor is stopped (4) and direct current
Motor (3) is connected, and encoder (5) is connected positioned at direct current generator (3) rear end, encoder (5) with controller (6), and controller (6) leads to
Cross control line or remote control (7) is connected with direct current generator (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046654.3A CN106677907A (en) | 2016-11-23 | 2016-11-23 | Aero-engine high-pressure rotor electric rocking-turning tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046654.3A CN106677907A (en) | 2016-11-23 | 2016-11-23 | Aero-engine high-pressure rotor electric rocking-turning tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106677907A true CN106677907A (en) | 2017-05-17 |
Family
ID=58866486
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611046654.3A Pending CN106677907A (en) | 2016-11-23 | 2016-11-23 | Aero-engine high-pressure rotor electric rocking-turning tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106677907A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107941519A (en) * | 2017-11-17 | 2018-04-20 | 贵州凯阳航空发动机有限公司 | A kind of aero-engine rotating equipment |
| CN109470483A (en) * | 2018-12-14 | 2019-03-15 | 中国航发沈阳发动机研究所 | Aircraft engine high pressure rotor rocking-turn power device and rocking-turn system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06213005A (en) * | 1993-01-13 | 1994-08-02 | Ishikawajima Harima Heavy Ind Co Ltd | Fan stall preventing device |
| CN201251451Y (en) * | 2008-09-19 | 2009-06-03 | 成都航利航空科技有限责任公司 | Electric positioning driving device for high-low voltage vane check of aeroengine |
| CN102913291A (en) * | 2012-10-31 | 2013-02-06 | 上海诚动液压科技发展有限公司 | Novel valve electric servo actuator with safe quick-closing function |
| CN204165751U (en) * | 2014-11-11 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of Aero-engine Bearing failure diagnosis data collection device |
| CN204406262U (en) * | 2015-01-14 | 2015-06-17 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aircraft engine high pressure rotor rocking-turn equipment |
-
2016
- 2016-11-23 CN CN201611046654.3A patent/CN106677907A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06213005A (en) * | 1993-01-13 | 1994-08-02 | Ishikawajima Harima Heavy Ind Co Ltd | Fan stall preventing device |
| CN201251451Y (en) * | 2008-09-19 | 2009-06-03 | 成都航利航空科技有限责任公司 | Electric positioning driving device for high-low voltage vane check of aeroengine |
| CN102913291A (en) * | 2012-10-31 | 2013-02-06 | 上海诚动液压科技发展有限公司 | Novel valve electric servo actuator with safe quick-closing function |
| CN204165751U (en) * | 2014-11-11 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of Aero-engine Bearing failure diagnosis data collection device |
| CN204406262U (en) * | 2015-01-14 | 2015-06-17 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aircraft engine high pressure rotor rocking-turn equipment |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107941519A (en) * | 2017-11-17 | 2018-04-20 | 贵州凯阳航空发动机有限公司 | A kind of aero-engine rotating equipment |
| CN109470483A (en) * | 2018-12-14 | 2019-03-15 | 中国航发沈阳发动机研究所 | Aircraft engine high pressure rotor rocking-turn power device and rocking-turn system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170517 |