CN114313302A - High-reliability aero-engine power outer cover opening actuating system and method - Google Patents
High-reliability aero-engine power outer cover opening actuating system and method Download PDFInfo
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- CN114313302A CN114313302A CN202111592212.XA CN202111592212A CN114313302A CN 114313302 A CN114313302 A CN 114313302A CN 202111592212 A CN202111592212 A CN 202111592212A CN 114313302 A CN114313302 A CN 114313302A
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000010276 construction Methods 0.000 claims 1
- 230000002035 prolonged effect Effects 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 7
- 239000003921 oil Substances 0.000 description 16
- 230000009471 action Effects 0.000 description 6
- 230000005484 gravity Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
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Abstract
The invention belongs to the field of hydraulic pressure, and discloses a high-reliability system and a method for opening and actuating a power outer cover of an aero-engine, wherein the system comprises a controller, a motor pump, a control valve, an actuator and a follow-up support rod; all set up an actuator and follow-up vaulting pole under every fan casing and the backstepping cover, the controller is connected and is controlled the motor pump, and the motor pump drives every actuator work and struts corresponding fan casing or backstepping cover respectively through the control valve, and the follow-up vaulting pole struts and prolongs and the follow-up supports along with corresponding fan casing or backstepping cover struts. The technical scheme for opening and actuating the power outer cover of the high-reliability aircraft engine can solve the problems that a fan cover is manually opened and reverse thrust is difficult when a large engine needs ground maintenance; the invention combines a plurality of supporting modes, has high reliability and solves the potential safety hazard.
Description
Technical Field
The invention belongs to the field of hydraulic pressure, relates to a high-reliability aero-engine power outer cover opening actuating technical scheme, and particularly relates to a high-reliability aero-engine power outer cover opening actuating system and method.
Background
The fan cover and the reverse thrust cover of the large aircraft engine are heavy, the engine cannot be opened in a manual mode when being maintained on the ground, and the fan cover and the reverse thrust cover need to be opened by utilizing one set of actuating system, so that maintenance personnel can maintain or repair the engine on the ground. In the open state of the fan casing and the thrust reverser casing, the actuation system must have a high degree of reliability in order to ensure the safety of the maintenance personnel and to prevent damage to the equipment.
The traditional technical scheme is that an actuating cylinder is matched with a manual support rod, the actuating cylinder is firstly used for propping open a fan cover and a reverse thrust cover, and then the manual support rod is used for propping up the fan cover and the reverse thrust cover.
The above-mentioned conventional solutions have the following disadvantages: firstly, in the process, the actuating cylinders need to be continuously pressurized to work, so that the manual support rods can be manually installed, two persons are needed to cooperate to complete the work, one person continuously controls the actuating cylinders, and the other person installs the manual support rods; the second problem is the problem of security, and the fan casing of traditional technical scheme and the state of strutting of backstepping cover are all accomplished the support by manual bracing piece promptly, do not have the safeguard, and maintenance personal work is in fan casing and backstepping cover below, if manual bracing piece goes out the problem and will bring very big potential safety hazard.
Disclosure of Invention
The purpose of the invention is: in order to solve the problems, the invention provides a high-reliability aero-engine power outer cover opening actuating system and a method, which are used for opening a fan cover and a reverse thrust cover during ground maintenance of a large-scale engine, can solve the problems that the fan cover is manually opened and the reverse thrust is difficult when the large-scale engine needs ground maintenance and repair, and have high reliability.
The technical scheme of the invention is as follows:
a high-reliability aero-engine power outer cover opening actuating system comprises a controller, a motor pump, a control valve, an actuator and a follow-up support rod; all set up an actuator and follow-up vaulting pole under every fan casing and the backstepping cover, the controller is connected and is controlled the motor pump, and the motor pump drives every actuator work and struts corresponding fan casing or backstepping cover respectively through the control valve, and the follow-up vaulting pole struts and prolongs and the follow-up supports along with corresponding fan casing or backstepping cover struts.
Further, the actuator is an actuator with a locking function, when the support rod of the actuator rises to the highest position, the support rod of the actuator falls back to be limited, and the actuator keeps the unfolding state without hydraulic support.
Furthermore, the fan cover support device further comprises manual support rods, and when each fan cover is completely unfolded, the manual support rods are arranged to assist in supporting.
Furthermore, the manual stay bar is of a telescopic structure, and a mechanical lock is arranged inside the manual stay bar.
Furthermore, the fan cover is divided into a left fan cover and a right fan cover, the reverse thrust cover is divided into a left reverse thrust cover and a right reverse thrust cover, four corresponding control buttons are arranged on the controller, and the four corresponding control buttons correspond to the support control of different fan covers and the reverse thrust cover.
Furthermore, the motor pump is respectively connected with actuators of the left fan cover, the right fan cover, the left backstepping cover and the right backstepping cover through four control valves, and the four control valves are independently controlled by four control buttons of the controller.
Further, the motor in the motor pump is an alternating current asynchronous motor.
Further, an oil outlet of the motor pump is provided with a safety valve.
A high-reliability method for starting and actuating a power outer cover of an aircraft engine comprises the steps of starting a power supply of a controller, starting a motor pump, starting an actuator of a fan cover in sequence, and starting the actuator of a thrust reverser after the fan cover is completely opened and fixed to finish the opening and fixing of the thrust reverser.
The invention has the advantages that:
1. the technical scheme for opening and actuating the power outer cover of the high-reliability aircraft engine can solve the problems that a fan cover is manually opened and reverse thrust is difficult when a large engine needs ground maintenance;
2. through the combination of multiple supporting modes, the device has high reliability and solves the potential safety hazard.
Drawings
FIG. 1 is a schematic diagram of a highly reliable aero-engine power cover opening actuation scheme of the present invention;
the system comprises a controller 1, a motor pump 2, an oil tank 3, a fan control valve 4, a reverse thrust control valve 5, a follow-up support rod 6, an actuator 7 and a manual support rod 8.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A high-reliability aero-engine power outer cover opening actuating system comprises a controller 1, a motor pump 2, a control valve, an actuator 7 and a follow-up support rod 8; all set up an actuator 7 and follow-up vaulting pole 8 under every fan casing and the backstepping cover, motor pump 2 is connected and controlled to controller 1, and motor pump 2 drives every actuator 7 work and struts corresponding fan casing or backstepping cover respectively through the control valve, and follow-up vaulting pole 8 struts and prolongs and the follow-up supports along with corresponding fan casing or backstepping cover struts.
The actuator 7 is an actuator having a locking function, and when the stay of the actuator 7 is raised to the highest position, the stay of the actuator 7 is restrained from falling, and at this time, the actuator 7 is kept in the deployed state without hydraulic support.
The fan cover support structure further comprises manual support rods 9, and when each fan cover is completely unfolded, the manual support rods 9 are arranged for auxiliary support.
The manual stay bar 8 is a telescopic structure, and a mechanical lock is arranged inside the manual stay bar 8.
The fan casing divide into left fan casing and right fan casing, and the backstepping cover divide into left backstepping cover and right backstepping cover, has corresponding four control button on the controller 1, corresponds the support control of different fan casings and backstepping covers.
The motor pump 2 is respectively connected with actuators 7 of the left fan cover, the right fan cover, the left backstepping cover and the right backstepping cover through four control valves, and the four control valves are independently controlled by four control buttons of the controller 1.
The motor in the motor pump 2 is an ac asynchronous motor.
The oil outlet of the motor pump 2 is provided with a safety valve.
A high-reliability method for starting and actuating a power outer cover of an aircraft engine comprises the steps of starting a power supply of a controller, starting a motor pump, starting an actuator of a fan cover in sequence, and starting the actuator of a thrust reverser after the fan cover is completely opened and fixed to finish the opening and fixing of the thrust reverser.
The invention is explained in further detail below with reference to the drawings.
As shown in fig. 1, a high-reliability aero-engine power outer cover opening actuating technical scheme comprises a controller 1, a motor pump 2, an oil tank 3, a fan cover control valve 4, a reverse thrust control valve 5, a follow-up stay bar 6, a fan cover actuator 7, a manual stay bar 8, a reverse thrust actuator 7, a left fan cover button, a right fan cover button, a left reverse thrust cover button and a right reverse thrust cover button; the follow-up support rod 6 consists of a shell assembly and a piston assembly, a locking mechanism is integrated in the follow-up support rod, and the piston assembly can be locked when the follow-up support rod is in a fully extended state; the thrust reverser 7 is composed of a shell component and a piston component, and a locking/unlocking mechanism is integrated in the thrust reverser, and can lock/unlock the piston component in a fully extended state; the controller 1 receives switching signal instructions of the left fan cover button, the right fan cover button, the left reverse thrust cover button and the right reverse thrust cover button, and controls the starting and stopping of the motor pump 2, the on-off of the fan cover control valve 4 and the on-off of the reverse thrust control valve 5; the motor pump 2 sucks working medium such as hydraulic oil from an oil tank 3, pressurizes the working medium to high pressure, and sends the working medium to a fan cover control valve 4 and a reverse control valve 5; the fan cover control valve 4 controls the oil ports of the fan cover actuators 7 of the left fan cover and the right fan cover to be switched between high-pressure working media and low-pressure working media, so that the fan cover actuators can extend out and retract under the action of external load; the reverse control valve 4 controls the oil port of a reverse actuator 9 on the left reverse thrust and the right reverse thrust to be switched between a high-pressure working medium and a low-pressure working medium, so that the reverse actuator is extended and retracted under the action of an external load; one end of the follow-up stay bar 6 is hinged with the load left fan cover, the load right fan cover, the load left reverse thrust and the load right reverse thrust, and the other end of the follow-up stay bar is hinged with the engine case; one end of the fan cover actuator 7 is hinged with the left load fan cover and the right load fan cover, and the other end is hinged with the engine case; one end of the reverse thrust actuator 7 is hinged with the load left reverse thrust and the load right reverse thrust, and the other end of the reverse thrust actuator is hinged with the engine case; one end of the manual stay bar 8 is hinged with the left fan cover and the right fan cover, and the other end is hinged with the engine case.
The motor in the motor pump 2 adopts an alternating current asynchronous motor;
an oil outlet of the motor pump 2 is provided with a safety valve;
a safety valve is arranged at an oil inlet of the reverse thrust actuator 7;
the fan cover is opened first, and then the reverse thrust is opened.
A high-reliability aero-engine power outer cover opening actuating technical scheme comprises the following opening working processes:
firstly, electrifying a controller 1;
secondly, pressing down a left fan cover button/a right fan cover button, electrifying a motor pump 2 and a fan cover electromagnetic valve 4, and driving high-pressure oil liquid to enter a fan cover actuator 7 to drive the fan cover actuator 7 to extend out;
thirdly, when the fan cover actuator 7 extends to the limit position, the follow-up stay bar 6 connecting the left fan cover/the right fan cover is drawn to extend to the limit position and locked;
fourthly, releasing the left fan cover button/the right fan cover button, powering off the motor pump 2 and the fan cover electromagnetic valve 4, returning oil through the fan cover actuator 7 under low pressure, slightly withdrawing the fan cover actuator 7 under the action of the gravity of the fan cover, and locking a mechanical lock in the actuator;
fifthly, mounting a manual support rod 8;
sixthly, pressing down the left/right reverse push button, electrifying the motor pump 2 and the reverse push electromagnetic valve 5, and enabling high-pressure oil to enter the reverse push actuator 7 to drive the reverse push actuator 7 to extend out;
seventhly, when the reverse-thrust actuator 7 extends to the limit position, the follow-up stay bar 6 connected with the reverse thrust is drawn to extend to the limit position and locked;
and step eight, releasing the left/right reverse push button, powering off the motor pump 2 and the reverse push solenoid valve 5, enabling the reverse push actuator 7 to return oil at low pressure, slightly withdrawing the reverse push actuator 7 under the action of reverse push gravity, and locking a mechanical lock in the actuator.
A high-reliability aero-engine power outer cover opening actuating technical scheme comprises the following closing working processes:
firstly, electrifying a controller 1;
secondly, manually unlocking a follow-up support rod 6 connected with a reverse thrust;
thirdly, pressing down the left/right reverse push buttons, enabling the reverse push actuator 7 to be completely extended out, and unlocking an internal mechanical lock;
fourthly, releasing the left reverse push button and the right reverse push button, powering off the motor pump 2 and the reverse push solenoid valve 5, turning on the reverse push actuator 7 to return oil at low pressure, and withdrawing the reverse push actuator 7 under the action of reverse push gravity;
fifthly, manually unlocking the manual support rod 8;
sixthly, manually unlocking a follow-up support rod 6 connected with the fan cover;
seventhly, pressing down the left fan cover button/the right fan cover button, electrifying the motor pump 2 and the fan cover electromagnetic valve 4, enabling high-pressure oil to enter the fan cover actuator 7, driving the fan cover actuator 7 to extend out, and unlocking an internal mechanical lock;
and seventhly, releasing the left fan cover button/the right fan cover button, powering off the motor pump 2 and the fan cover electromagnetic valve 4, returning oil through the low-pressure fan cover actuator 7, and withdrawing the fan cover actuator 7 under the action of the gravity of the fan cover.
Claims (9)
1. A high-reliability aero-engine power outer cover opening actuating system is characterized by comprising a controller (1), a motor pump (2), a control valve, an actuator (7) and a follow-up support rod (8); all set up one actuator (7) and follow-up vaulting pole (8) under every fan casing and the anti-cover that pushes away, motor pump (2) are connected and are controlled in controller (1), and motor pump (2) drive every actuator (7) work respectively and strut corresponding fan casing or anti-cover that pushes away through the control valve, and follow-up vaulting pole (8) are strutted and are prolonged and follow-up support along with corresponding fan casing or anti-cover that pushes away.
2. A highly reliable aero-engine power cover opening actuation system according to claim 1 wherein the actuator (7) is an actuator with a locking function, when the stay of the actuator (7) is raised to the uppermost position, the stay of the actuator (7) is restrained from falling back, and the actuator (7) is maintained in the deployed state without hydraulic support.
3. The high-reliability aircraft engine power cover opening actuating system according to claim 1, characterized by further comprising a manual stay bar (9), wherein when each fan cover is completely unfolded, the manual stay bar (9) is arranged for auxiliary support.
4. A highly reliable aircraft engine power cover opening actuation system according to claim 3, characterised in that the manual stay (8) is of telescopic construction, the manual stay (8) being provided internally with a mechanical lock.
5. The high reliability aircraft engine power cover opening actuation system of claim 1, characterized in that the fan housing is divided into a left fan housing and a right fan housing, the thrust reverser is divided into a left thrust reverser and a right thrust reverser, and the controller (1) has four corresponding control buttons corresponding to the support controls of the different fan housings and thrust reversers.
6. A highly reliable aircraft engine power cover opening actuation system according to claim 5, characterized in that the motor pump (2) is connected to the actuators (7) of the left fan cover, the right fan cover, the left thrust reverser and the right thrust reverser respectively, through four control valves, which are controlled individually by four control buttons of the controller (1).
7. A highly reliable aircraft engine power cover opening actuation system according to claim 1, characterised in that the electric motor in the motor pump (2) is an ac asynchronous motor.
8. A highly reliable aeroengine power housing opening actuation system according to claim 1, characterized in that the oil outlet of the motor pump (2) is provided with a safety valve.
9. A high-reliability aero-engine power cover opening actuating method is characterized in that a high-reliability aero-engine power cover opening actuating system as claimed in any one of claims 1 to 8 is used, a power supply of a controller is turned on, a motor pump is started, an actuator of a fan cover is turned on first, and an actuator of a thrust reverser is turned on after the fan cover is completely opened and fixed, so that the opening and fixing of the thrust reverser are completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592212.XA CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592212.XA CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
Publications (2)
| Publication Number | Publication Date |
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| CN114313302A true CN114313302A (en) | 2022-04-12 |
| CN114313302B CN114313302B (en) | 2023-12-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111592212.XA Active CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
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Citations (10)
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|---|---|---|---|---|
| US20030044266A1 (en) * | 2001-08-31 | 2003-03-06 | Sieto Vandillen | Power rear door interface for a vehicle having a rear entry folding ramp |
| US20040238687A1 (en) * | 2003-06-02 | 2004-12-02 | Emlyn Jones | Aeroengine nacelle |
| US20090065634A1 (en) * | 2005-06-16 | 2009-03-12 | Aircelle | Control system for the nacelle of a turboreactor |
| CN103158874A (en) * | 2011-12-08 | 2013-06-19 | 空中客车营运有限公司 | Substitution device for aircraft engine |
| US20140075918A1 (en) * | 2012-09-19 | 2014-03-20 | United Technologies Corporation | Nacelle leading edge electrical latching system |
| US20150369083A1 (en) * | 2013-03-14 | 2015-12-24 | United Technologies Corporation | Latching actuation mechanism for nacelle mounted latching system |
| US20160229546A1 (en) * | 2013-09-19 | 2016-08-11 | Sagem Defense Securite | Telescopic actuator and aircraft engine comprising such an actuator |
| CN109026436A (en) * | 2018-08-22 | 2018-12-18 | 中国商用飞机有限责任公司 | It is counter to push away acting device and turbojet nacelle |
| US20190168884A1 (en) * | 2016-06-14 | 2019-06-06 | C Series Aircraft Limited Partnership | System for and method of actuating an aircraft cowl |
| CN112824663A (en) * | 2019-11-20 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
-
2021
- 2021-12-23 CN CN202111592212.XA patent/CN114313302B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030044266A1 (en) * | 2001-08-31 | 2003-03-06 | Sieto Vandillen | Power rear door interface for a vehicle having a rear entry folding ramp |
| US20040238687A1 (en) * | 2003-06-02 | 2004-12-02 | Emlyn Jones | Aeroengine nacelle |
| US20090065634A1 (en) * | 2005-06-16 | 2009-03-12 | Aircelle | Control system for the nacelle of a turboreactor |
| CN103158874A (en) * | 2011-12-08 | 2013-06-19 | 空中客车营运有限公司 | Substitution device for aircraft engine |
| US20140075918A1 (en) * | 2012-09-19 | 2014-03-20 | United Technologies Corporation | Nacelle leading edge electrical latching system |
| US20150369083A1 (en) * | 2013-03-14 | 2015-12-24 | United Technologies Corporation | Latching actuation mechanism for nacelle mounted latching system |
| US20160229546A1 (en) * | 2013-09-19 | 2016-08-11 | Sagem Defense Securite | Telescopic actuator and aircraft engine comprising such an actuator |
| US20190168884A1 (en) * | 2016-06-14 | 2019-06-06 | C Series Aircraft Limited Partnership | System for and method of actuating an aircraft cowl |
| CN109026436A (en) * | 2018-08-22 | 2018-12-18 | 中国商用飞机有限责任公司 | It is counter to push away acting device and turbojet nacelle |
| CN112824663A (en) * | 2019-11-20 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
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| Publication number | Publication date |
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| CN114313302B (en) | 2023-12-08 |
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