CN209458191U - Propeller regulating mechanism - Google Patents
Propeller regulating mechanism Download PDFInfo
- Publication number
- CN209458191U CN209458191U CN201920147486.XU CN201920147486U CN209458191U CN 209458191 U CN209458191 U CN 209458191U CN 201920147486 U CN201920147486 U CN 201920147486U CN 209458191 U CN209458191 U CN 209458191U
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- plate
- central axis
- regulating mechanism
- shell
- connecting plate
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Abstract
Propeller regulating mechanism, installation and adjustment plate on central axis, it is located on the downside of adjustable plate on central axis and connecting plate is installed, connecting plate is loaded in the middle part of shell, it is located at connecting plate two sides on shell and two guide plates is installed respectively, guide plate is equipped with arc groove, adjusts ring and is slidably mounted in the groove of two guide plates by screw, and adjustable plate connection adjusts ring.The propeller regulating mechanism of the utility model during exercise due to mechanism is attached using external connecting rod with adjustable plate, greatly reduces friction, to eliminate the clamping stagnation problem of mechanism, more stable compared to traditional aero-engine, regulating effect is more preferable.
Description
Technical field
The utility model relates to aero-engine technology fields.
Background technique
Aero-engine is a kind of highly complex and accurate thermal machine, can directly affect aircraft safety, can
By property and economy.The control system of engine is referred to as " nervous system " of engine, and function is ensuring that engine exists
It can normally and reliably work under complicated service condition, and make engine performance maximizing the benefits.With engine
The raising of energy, compressor working condition is further close to stall margin.Engine surge, which is air-flow, flows into compressor with High Angle of Attack,
Serious separation is formed at blade back, the periodic swinging phenomenon for causing blower outlet stream pressure and flow to be pulsed strongly.When
When off-design point works, compressor just has surge may greatly occur engine, causes consequence very serious.To improve pressure
The working characteristics of mechanism of qi expands its stable operation range, there is anti-asthma vibration means on the axial flow compressor of high supercharging pressure level, by knot
Configuration formula can be divided into intermediate deflation structure, compressor inlet can be changed camber inlet guide vanes or transducible stream blade, can turn stator leaf
Piece, birotor and more rotor compressors and treated casing etc..
Adjustable vane is just applied before very early, early in the 1940s, the First whirlpool eruption that Germany develops
Just there is the application of adjustable stator blade (VariableStatorVane, abbreviation VSV) in motivation Jum0004.Later, this technology
In the military whirlpool of the states such as the United States, Russia, spray and fanjet obtain paying attention to and developing, or even be also apply to ground gas turbine etc.
Civil field.When engine is from a certain working condition to another working condition, VSV system controls guide vane or stator blade turns
It is dynamic, so that charge air flow is entered high-pressure compressor blade grid passage always with optimal angle, the air-flow angle of attack is suitable, front and back flow
Match, in this way it is possible to prevente effectively from occurring being vortexed or surge phenomenon, expands compressor stable operation range, reduce aerodynamic loss, mention
High aeroperformance.Compressor stator regulating mechanism (VariableStatorVaneSystem, hereinafter referred to as VSV regulating mechanism)
By adjusting inlet guide vane and adjustable stator blade angle to expand stability margin, improves overall engine efficiency, prevent
Compressor surge is the important component of aero-engine.
Currently, modern aeroengine use mostly multistage stator blade can conditioning technology, pass through adjust stator blade angle
Degree works so that rotor blade is under the angle of attack of satisfaction, so as to avoid surge, and makes compressor in the case where deviateing design conditions
It still ensures that rotor blade works under the angle of attack being satisfied in the main, improves the working characteristics of compressor, expand steady operation
Range.Propeller regulating mechanism seriously affects the functional reliability of engine, and the movement clamping stagnation being likely to occur will cause huge
Security risk.With the development of constantly bringing forth new ideas of propeller regulating mechanism, the control precision and reliability of its motion adjustment mechanism are mentioned
Higher requirement out, therefore study the transmission rule of propeller regulating mechanism, analysis manufacture, introduce in assembling process it is uncertain because
Influence of the element to blade kinematic accuracy, and then improving its reliability by optimization design is that the key technology in engine design is asked
Topic.
Existing propeller regulating mechanism has the following disadvantages, when adjusting blade rotating angle, the case where mechanism can generate clamping stagnation,
Blade conciliation is not in place, is unable to complete the tasks such as control air inlet；Mechanism is unstable at runtime, and engine is made the feelings of surge occur
Condition.
Utility model content
In order to solve the problems, such as to move clamping stagnation, fluctuation of service existing for existing propeller regulating mechanism, the utility model is mentioned
A kind of propeller regulating mechanism is supplied.
The utility model technical solution used for the above purpose is: propeller regulating mechanism, installs on central axis
Adjustable plate is located on the downside of adjustable plate on central axis and installs connecting plate, and connecting plate is located at connecting plate two loaded in the middle part of shell on shell
Two guide plates are installed in side respectively, and guide plate is equipped with arc groove, adjust ring by screw and are slidably mounted on two guide plates
Groove in, adjustable plate connection adjust ring.
The central axis top passes through fixing bolt installation and adjustment plate.
Supporting mechanism is diametrically equipped in the shell, supporting mechanism lower end connects central axis pedestal.
The propeller regulating mechanism of the utility model, during exercise due to mechanism, using external connecting rod and adjustable plate into
Row connection, greatly reduces friction, to eliminate the clamping stagnation problem of mechanism, compared to traditional aero-engine, more surely
Fixed, regulating effect is more preferable.
Detailed description of the invention
Fig. 1 is the utility model propeller regulating mechanism main structure figure.
Fig. 2 is the utility model propeller regulating mechanism overlooking structure figure.
Fig. 3 is the utility model propeller regulating mechanism central axis portion main structure figure.
In figure: 1, central axis, 2, bolt, 3, shell, 4, support construction, 5, adjustable plate, 6, adjusting ring, 7, guide plate, 8,
Connecting plate, 9, groove, 10, fixing bolt.
Specific embodiment
The propeller regulating mechanism structure of the utility model is as shown in Figure 1-3,1 top of central axis is installed by fixing bolt 10
Adjustable plate 5 is located on the downside of adjustable plate 5 on central axis 1 and installs connecting plate 8, and connecting plate 8 is located at loaded on 3 middle part of shell on shell 3
Two guide plates 7 are installed in 8 two sides of connecting plate respectively, and guide plate 7 is equipped with arc groove 9, adjust ring 6 and pass through the sliding peace of screw 2
In groove 9 loaded on two guide plates 7, the connection of adjustable plate 5 adjusts ring 6, and supporting mechanism 4, branch are diametrically equipped in shell 3
4 lower end of support mechanism connects 1 pedestal of central axis.
Mechanism principle: mechanism is fixed by shell 3 and support construction 4, and adjustable plate 5 is bolted with adjusting ring 6 by row,
When external force drives adjusting ring 6, the bolt 2 for adjusting ring two sides is moved in the groove 9 of guide plate 7, thus band
Dynamic adjustable plate 5 is rotated, and the central axis being connected with adjustable plate 51 is rotated, and blade (not shown) is connected on central axis,
The rotation angle of central axis 1 need to be only adjusted, the rotation angle of central axis 1 is exactly the adjusting angle of blade.
Claims (3)
1. propeller regulating mechanism, it is characterised in that: installation and adjustment plate (5) on central axis (1) is located at adjustable plate on central axis (1)
(5) connecting plate (8) are installed in downside, and connecting plate (8) is installed in the middle part of shell (3), and connecting plate (8) two sides point are located on shell (3)
Not An Zhuan two guide plates (7), guide plate (7) is equipped with arc groove (9), adjusts ring (6) and be slidably mounted on by screw (2)
In the groove (9) of two guide plates (7), adjustable plate (5) connection adjusts ring (6).
2. propeller regulating mechanism according to claim 1, it is characterised in that: central axis (1) top passes through fixed spiral shell
Bolt (10) installation and adjustment plate (5).
3. propeller regulating mechanism according to claim 1, it is characterised in that: be diametrically equipped in the shell (3)
Supporting mechanism (4), supporting mechanism (4) lower end connect central axis (1) pedestal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920147486.XU CN209458191U (en) | 2019-01-28 | 2019-01-28 | Propeller regulating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920147486.XU CN209458191U (en) | 2019-01-28 | 2019-01-28 | Propeller regulating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209458191U true CN209458191U (en) | 2019-10-01 |
Family
ID=68045995
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920147486.XU Expired - Fee Related CN209458191U (en) | 2019-01-28 | 2019-01-28 | Propeller regulating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209458191U (en) |
-
2019
- 2019-01-28 CN CN201920147486.XU patent/CN209458191U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191001 Termination date: 20210128 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |