CN114136628B - Throttle lever limiting device with adjustable test angle of aero-engine - Google Patents
Throttle lever limiting device with adjustable test angle of aero-engine Download PDFInfo
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- CN114136628B CN114136628B CN202111223497.XA CN202111223497A CN114136628B CN 114136628 B CN114136628 B CN 114136628B CN 202111223497 A CN202111223497 A CN 202111223497A CN 114136628 B CN114136628 B CN 114136628B
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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
- G01M15/02—Details or accessories of testing apparatus
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/40—Engine management systems
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
Abstract
The application provides an aeroengine test angle adjustable throttle lever limiting device, which belongs to the technical field of aeroengine tests and specifically comprises an arc limiting plate, an automatic limiting assembly and a set screw, wherein the plane side of the arc limiting plate is in threaded connection with a throttle lever; the plane side of the arc limiting plate is provided with a first arc chute, and the automatic limiting assembly penetrates into the first arc chute from the direction opposite to the throttle lever and can slide along the first arc chute; the protruding side of arc limiting plate is equipped with the second arc spout, the second arc spout with first arc spout communicates with each other, set screw penetrates in the second arc spout with automatic spacing subassembly is connected and is right automatic spacing subassembly carries out the angle spacing. Through the processing scheme of the application, the quick conversion of the engine throttle lever at any angle is realized, good structural strength can be ensured, and engineering realizability is strong.
Description
Technical Field
The application relates to the technical field of aero-engine tests, in particular to an adjustable throttle lever limiting device for an aero-engine test angle.
Background
The whole machine test of the aero-engine is an important means for carrying out comprehensive technical analysis on the aero-engine, and in the whole machine ground test and the whole machine high-altitude simulation test, an accelerator lever for controlling the engine is necessary equipment for controlling the engine state and carrying out emergency treatment on the engine. Meanwhile, in some specific experiments, the engine is required to be rapidly converted in a short time limit under different states, and the operation has high operation requirements on field technicians, so that a device capable of rapidly and accurately converting any angle of the throttle lever and simultaneously using the existing functions of the throttle lever is urgently needed.
Disclosure of Invention
In view of this, this application embodiment provides an aeroengine test angularly adjustable throttle lever stop device, is the stop gear who reequips to the form of present throttle lever, and this mechanism not only can realize the spacing of throttle lever angle, possesses simultaneously that restriction angle is adjustable, install fast and two kinds of restriction angles function that use simultaneously, at least part solves the problem that exists among the prior art.
The embodiment of the application provides an aeroengine test angle adjustable throttle lever limiting device, which comprises an arc limiting plate, an automatic limiting assembly and a set screw, wherein the plane side of the arc limiting plate is in threaded connection with a throttle lever;
the plane side of the arc limiting plate is provided with a first arc chute, and the automatic limiting assembly penetrates into the first arc chute from the direction opposite to the throttle lever and can slide along the first arc chute;
the protruding side of arc limiting plate is equipped with the second arc spout, the second arc spout with first arc spout communicates with each other, set screw penetrates in the second arc spout with automatic spacing subassembly is connected and is right automatic spacing subassembly carries out the angle spacing.
According to a specific implementation manner of the embodiment of the application, the automatic limiting assembly comprises a limiting pin and a pin sleeve sleeved outside the limiting pin, one end of the limiting pin is provided with a protrusion, the other end of the limiting pin is provided with a limiting pin flange, and the pin sleeve is positioned between the protrusion and the limiting pin flange; the automatic limiting assembly comprises a limiting pin flange, a pin sleeve and a limiting pin sleeve, wherein a first elastic member is arranged between the pin sleeve and the limiting pin flange, an annular groove is arranged on the limiting pin, a positioning pin is arranged at the position, corresponding to the groove, of the pin sleeve vertically, the positioning pin can fall into the groove through moving the pin sleeve, the automatic limiting assembly is rapidly limited, and after the positioning pin is pulled out, the limiting pin automatically rebounds, so that the automatic limiting assembly is rapidly recovered.
According to a specific implementation manner of the embodiment of the application, the pin sleeve is vertically provided with a protruding groove, the outer side of the protruding groove is sleeved with a positioning pin cover, and one end of the positioning pin penetrates through the positioning pin cover and the protruding groove to fall into the groove; the locating pin is close to one side of the groove is provided with a locating ring, the upper side of the locating ring is provided with a second elastic component surrounding the locating pin, the upper end of the second elastic component abuts against the locating pin cover, and the lower end of the second elastic component abuts against the locating ring.
According to a specific implementation manner of the embodiment of the application, when the positioning pin falls into the groove, the distance between the positioning ring and the end part of the positioning pin, which is close to the groove, is greater than the sum of the depth of the groove and the thickness of the pin bush.
According to a specific implementation manner of the embodiment of the application, the pin bush is provided with a set screw connecting hole close to one side of the protrusion, and the set screw is connected with the first arc-shaped groove through the set screw connecting hole.
According to a specific implementation manner of the embodiment of the application, a locating pin flange is arranged at one end, away from the groove, of the locating pin.
According to a specific implementation manner of the embodiment of the application, a sliding groove is formed in the pin bush, which is close to one side of the protrusion, and when the positioning pin is pulled up, the protrusion can slide into the sliding groove and is limited by the end face of the sliding groove.
According to a specific implementation manner of the embodiment of the application, the first elastic member is a first spring.
A specific implementation manner of the embodiment of the present application is characterized in that the second elastic member is a second spring.
Advantageous effects
According to the throttle lever limiting device with the adjustable test angle for the aero-engine, the limiting angle can be adjusted randomly by adopting a sliding block design mode based on the arc-shaped groove guide rail principle, and the structure is simple and reliable, and the adjustment is quick and convenient; the locking mode of the set screw is adopted, so that the operation is simple and easy; the spring limiting and pre-tightening design mode is adopted, so that the limiting pin can be automatically limited, the design is ingenious, and the use is convenient; the limiting device does not damage the structure and the function of the original throttle lever, and has the characteristics of convenient installation and easy popularization.
The throttle lever limiting device capable of being adjusted steplessly for the aeroengine test is reasonable in structural design and simple and compact in structure. The accelerator lever with the position device can realize the rapid conversion of the engine accelerator lever at any angle, ensure good structural strength, has strong engineering realization property and has good application effect in the aeroengine test.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of an aero-engine test angle adjustable throttle lever stop in accordance with an embodiment of the present invention;
fig. 2 is a cross-sectional view of a self-limiting assembly according to one embodiment of the present invention.
In the figure: 1. fixing round screws; 2. an arc limiting plate; 3. a set screw; 4. an automatic limiting component; 4-1, a limiting pin flange; 4-2, limiting pins; 4-3, pin sleeve; 4-4, locating pin flanges; 4-5, locating pin covers; 4-6, locating pins; 4-7, a second elastic member; 4-8, a first elastic member; 4-9, grooves; 4-10, a set screw connecting hole; 4-11, a first arc chute matching position.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides an aeroengine test angle adjustable throttle lever stop device, including arc limiting plate 2, automatic spacing subassembly 4 and holding screw 3, the plane side and the throttle lever threaded connection of arc limiting plate 2, specific, the plane side of arc limiting plate 2 is connected with the throttle lever through fixed round screw 1, in other words, this throttle lever stop device installs the use through changing former throttle lever round screw into the fixed round screw 1 of this device, does not destroy original throttle lever structure and function.
The plane side of the arc limiting plate 2 is provided with a first arc chute, and the automatic limiting assembly 4 penetrates into the first arc chute from the direction opposite to the throttle lever and can slide along the first arc chute. Specifically, the arc flow direction of the first arc chute is matched with the arc flow direction of the arc limiting plate 2.
The convex side of the arc-shaped limiting plate 2 is provided with a second arc-shaped sliding groove which is communicated with the first arc-shaped sliding groove, the set screw 3 penetrates into the second arc-shaped sliding groove to be connected with the automatic limiting component 4, the angle of the automatic limiting component 4 can be limited by screwing the set screw 3, the automatic limiting component 4 moves along the first arc-shaped sliding groove, and the limiting of any angle can be realized by the set screw 3; meanwhile, by adjusting the automatic limiting component 4, the quick automatic limiting and quick automatic recovery of the throttle lever limiting device can be realized.
More specifically, the automatic limiting assembly 4 comprises a limiting pin 4-2 and a pin sleeve 4-3 sleeved outside the limiting pin 4-2, and referring to fig. 2 for specific structure, one end of the limiting pin 4-2 is provided with a protrusion, the other end is provided with a limiting pin flange 4-1, the pin sleeve 4-3 is positioned between the protrusion and the limiting pin flange 4-1, and the protrusion and the limiting pin flange 4-1 play a limiting role on the pin sleeve 4-3; a first elastic component 4-8 is arranged between the pin sleeve 4-3 and the flange of the limiting pin 4-2, and the first elastic component 4-8 applies axial pretightening force to the limiting pin 4-2. A first arc-shaped chute matching position 11 is arranged on one side, close to the bulge, of the pin sleeve 4-3, and the first arc-shaped chute matching position 11 slides in the first arc-shaped chute.
A circle of annular grooves 4-9 are formed in the circumferential direction of the limiting pin 4-2, positioning pins 4-6 are vertically arranged at positions, corresponding to the grooves 4-9, of the pin sleeves 4-3, when the limiting pin flange 4-1 is lightly pushed, the pin sleeves 4-3 move relatively towards the limiting pin flange 4-1, the positioning pins 4-6 can fall into the grooves 4-9, quick limiting of the automatic limiting assembly 4 is achieved, and at the moment, the first elastic member 4-8 is compressed; after the locating pin 4-6 is pulled out, the locating pin flange 4-1 is driven to automatically rebound by the elastic force of the first elastic member 4-8, so that the automatic locating component 4 can be quickly restored.
In a preferred embodiment, the pin bush 4-3 is vertically provided with a protruding groove, the outer side of the protruding groove is sleeved with a positioning pin cover 4-5, and one end of the positioning pin 4-6 passes through the positioning pin cover 4-5 and the protruding groove and falls into the groove 4-9; a positioning ring is arranged on one side, close to the groove 4-9, of the positioning pin 4-6, a second elastic member 4-7 surrounding the positioning pin 4-6 is arranged on the upper side of the positioning ring, the upper end of the second elastic member 4-7 abuts against the positioning pin cover 4-5, the lower end of the second elastic member 4-7 abuts against the positioning ring, and the second elastic member 4-7 applies axial pretightening force to the positioning pin 4-6; when the locating pin 4-6 is pulled up, the second elastic component 4-7 is pressed, the locating ring on the locating pin 4-6 is subjected to the axial pretightening force of the second elastic component 4-7, and when the locating pin flange 4-1 is pushed, the locating pin 4-6 is just aligned with the groove 4-9, so that the locating pin can automatically fall into the groove 4-9, and the quick locating of the automatic locating component 4 is realized.
Specifically, when the positioning pin 4-6 falls into the groove 4-9, the distance between the positioning ring and the end of the positioning pin 4-6 close to the groove 4-9 is greater than the sum of the depth of the groove 4-9 and the thickness of the pin bush 4-3.
In one embodiment, the pin bush 4-3 is provided with a set screw connecting hole 4-10 near one side of the bulge, that is, a set screw connecting hole 4-10 is provided at the first arc chute matching position 4-11, and the set screw 3 connects the automatic limiting component 4 with the first arc chute through the set screw connecting hole 4-10.
Further, one end of the locating pin 4-6 far away from the groove 4-9 is provided with a locating pin 4-6 flange 4-4, so that the locating pin 4-6 can be conveniently pulled up.
Further, a sliding groove is formed in the pin bush 4-3 close to one side of the protrusion, and when the positioning pin 4-6 is pulled up, the protrusion can slide into the sliding groove and is limited by the end face of the sliding groove.
In this application, the first elastic member 4-8 or the second elastic member 4-7 may be provided as springs, respectively, a first spring and a second spring.
According to the embodiment provided by the invention, the limit angle can be adjusted at will by adopting a sliding block design mode based on the arc-shaped groove guide rail principle, the structure is simple and reliable, and the adjustment is quick and convenient; the locking mode of the set screw is adopted, so that the operation is simple and easy; the spring limiting and pre-tightening design mode is adopted, so that the limiting pin can be automatically limited, the design is ingenious, and the use is convenient; the limiting device does not damage the structure and the function of the original throttle lever, and has the characteristics of convenient installation and easy popularization.
The throttle lever limiting device capable of being adjusted steplessly for the aeroengine test is reasonable in structural design and simple and compact in structure. The accelerator lever with the position device can realize the rapid conversion of the engine accelerator lever at any angle, ensure good structural strength, has strong engineering realization property and has good application effect in the aeroengine test.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The throttle lever limiting device with the adjustable test angle for the aero-engine is characterized by comprising an arc limiting plate, an automatic limiting assembly and a set screw, wherein the plane side of the arc limiting plate is in threaded connection with the throttle lever through a fixed round screw;
the plane side of the arc limiting plate is provided with a first arc chute, and the automatic limiting assembly penetrates into the first arc chute from the direction opposite to the throttle lever and can slide along the first arc chute;
the bulge side of the arc-shaped limiting plate is provided with a second arc-shaped sliding groove, the second arc-shaped sliding groove is communicated with the first arc-shaped sliding groove, and the set screw penetrates into the second arc-shaped sliding groove to be connected with the automatic limiting assembly and conduct angle limiting on the automatic limiting assembly;
the automatic limiting assembly comprises a limiting pin and a pin sleeve sleeved outside the limiting pin, one end of the limiting pin is provided with a protrusion, the other end of the limiting pin is provided with a limiting pin flange, and the pin sleeve is positioned between the protrusion and the limiting pin flange; the automatic limiting assembly comprises a limiting pin flange, a pin sleeve and a limiting pin sleeve, wherein a first elastic member is arranged between the pin sleeve and the limiting pin flange, an annular groove is arranged on the limiting pin, a positioning pin is arranged at the position, corresponding to the groove, of the pin sleeve vertically, the positioning pin can fall into the groove through moving the pin sleeve, the automatic limiting assembly is rapidly limited, and after the positioning pin is pulled out, the limiting pin automatically rebounds, so that the automatic limiting assembly is rapidly recovered.
2. The throttle lever limiting device with the adjustable test angle for the aeroengine according to claim 1, wherein a protruding groove is vertically formed in the pin sleeve, a positioning pin cover is sleeved outside the protruding groove, and one end of the positioning pin penetrates through the positioning pin cover and the protruding groove to fall into the groove; the locating pin is close to one side of the groove is provided with a locating ring, the upper side of the locating ring is provided with a second elastic component surrounding the locating pin, the upper end of the second elastic component abuts against the locating pin cover, and the lower end of the second elastic component abuts against the locating ring.
3. The adjustable test angle throttle lever stop of claim 2, wherein when the locating pin falls into the groove, the distance between the locating ring and the end of the locating pin, which is close to the groove, is greater than the sum of the depth of the groove and the thickness of the pin bush.
4. The throttle lever limiting device with adjustable test angle for an aeroengine according to claim 1, wherein a set screw connecting hole is formed in one side, close to the protrusion, of the pin bush, and the set screw enables the automatic limiting assembly to be connected with the first arc-shaped sliding groove through the set screw connecting hole.
5. The adjustable test angle throttle lever stop of an aircraft engine of claim 1, wherein the end of the dowel remote from the recess is provided with a dowel flange.
6. The throttle lever limiting device with adjustable test angle for an aeroengine according to claim 1, wherein a chute is arranged in the pin bush near one side of the protrusion, and when the positioning pin is pulled up, the protrusion can slide into the chute and is limited by the end face of the chute.
7. The adjustable angle throttle lever stop of claim 1, wherein the first resilient member is a first spring.
8. The adjustable test angle throttle lever stop of an aircraft engine of claim 2, wherein the second resilient member is a second spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223497.XA CN114136628B (en) | 2021-10-20 | 2021-10-20 | Throttle lever limiting device with adjustable test angle of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223497.XA CN114136628B (en) | 2021-10-20 | 2021-10-20 | Throttle lever limiting device with adjustable test angle of aero-engine |
Publications (2)
| Publication Number | Publication Date |
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| CN114136628A CN114136628A (en) | 2022-03-04 |
| CN114136628B true CN114136628B (en) | 2023-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111223497.XA Active CN114136628B (en) | 2021-10-20 | 2021-10-20 | Throttle lever limiting device with adjustable test angle of aero-engine |
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| CN207938216U (en) * | 2017-09-28 | 2018-10-02 | 四川偌特航空科技有限公司 | Fixed-wing flight simulator throttle control mechanism |
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| US3839907A (en) * | 1973-03-30 | 1974-10-08 | Rca Corp | Engine performance analyzer using simulated load |
| JP3739891B2 (en) * | 1997-03-25 | 2006-01-25 | 三菱重工業株式会社 | Engine operation panel structure |
| JP2006183501A (en) * | 2004-12-27 | 2006-07-13 | Yamaha Motor Co Ltd | Misfire detecting device and method of engine and saddle-riding type vehicle |
| CN200979500Y (en) * | 2006-10-31 | 2007-11-21 | 扬动股份有限公司 | Throttle adjusting mechanism of diesel engine |
| CN102352796B (en) * | 2011-11-11 | 2013-07-31 | 湖南山河科技股份有限公司 | Accelerator and enrichment valve control mechanism of piston engine of light aircraft |
| US10099795B2 (en) * | 2015-11-04 | 2018-10-16 | Innovative Solutions & Support, Inc. | Precision operator for an aircraft autothrottle or autopilot system |
| CN105571761B (en) * | 2015-12-15 | 2018-04-10 | 中国燃气涡轮研究院 | A kind of parallel elastic connecting device for motor power measurement stand |
| CN109250129B (en) * | 2018-09-25 | 2021-09-14 | 陕西飞机工业（集团）有限公司 | Adjustable limiting device for aircraft engine in-air medium-small throttle |
| CN109606704A (en) * | 2018-12-11 | 2019-04-12 | 四川航空工业川西机器有限责任公司 | A kind of fax power control platform |
| CN212363653U (en) * | 2020-07-01 | 2021-01-15 | 昆明理工大学 | Testing arrangement of unmanned aerial vehicle engine parameter |
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| GB1122290A (en) * | 1966-02-07 | 1968-08-07 | Gen Electric | Improvements in standby afterburner operation system |
| CN104481705A (en) * | 2014-11-05 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Apparatus for controlling angle of aeroengine fuel-oil regulator by using steel rope |
| CN207938216U (en) * | 2017-09-28 | 2018-10-02 | 四川偌特航空科技有限公司 | Fixed-wing flight simulator throttle control mechanism |
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| CN114136628A (en) | 2022-03-04 |
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