CN201201716Y - Protector for propeller type airplane turbine engine - Google Patents
Protector for propeller type airplane turbine engine Download PDFInfo
- Publication number
- CN201201716Y CN201201716Y CNU2007201754406U CN200720175440U CN201201716Y CN 201201716 Y CN201201716 Y CN 201201716Y CN U2007201754406 U CNU2007201754406 U CN U2007201754406U CN 200720175440 U CN200720175440 U CN 200720175440U CN 201201716 Y CN201201716 Y CN 201201716Y
- Authority
- CN
- China
- Prior art keywords
- turbine engine
- engine
- blade
- guard
- airplane turbine
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides a blade type airplane turbine engine guard, which belongs to an airplane turbine engine guarding device. The blade type airplane turbine engine guard is provided with blades and an air inlet end, wherein the blades are similar to a beater head of a domestic pulper, the air inlet end is mounted on the airplane turbine engine, the blades are driven to rotate synchronously by an extension shaft of the airplane engine, the high-speed rotating blades can smash or knockout foreign matters entering the engine (such as birds), thereby protecting the engine. The blade type airplane turbine engine guard is reasonable in structure, and can effectively prevent birds entering the engine, thereby increasing flight safety and reducing probability of accidents.
Description
Technical field
The utility model provides a kind of later-model protective device, a kind of protective device that is used on the jet airplane.Be installed in the inlet end of jet engine, the protection driving engine.
Background technology
The inlet end of existing jet engine does not all have protective device, and flying bird usually can be inhaled into air inlet
, with making the flabellum distortion of turbine engine, perhaps block driving engine, make engine shutdown and even on fire.Destruction to Power System of Flight Vehicle usually is fatal, can directly cause aircraft stall to crash.Therefore, near existing airport, scarer to be set, in the landing process of aircraft, bump against preventing with flying bird.However, the incident that enters aircraft turbine engine such as flying bird still happens occasionally.
Summary of the invention
The utility model provides a kind of aircraft turbine engine guard; belong to a kind of aircraft turbine engine protective device; the making beating head that it has with the family expenses beater similarly rotates blade; inlet end-the aircraft turbine engine that is installed in aircraft turbine engine prolongs on the axle; blade drives rotation synchronously by the aircraft turbine engine axle; the turbine engine required air; before entering driving engine, at first to pass through this rotation blade; if be mingled with foreign matters such as flying bird in the inlet air; this rotation blade will smash and hit the foreign matter that may enter driving engine; even there is the foreign matter fragment that is crashed to pieces to enter driving engine again; infringement to driving engine is also very little, thereby has protected driving engine.This turbine engine guard, rational in infrastructure, can prevent effectively that flying bird from entering in the driving engine, thereby improve the safety of flight, reduced possibility of accident occurrence.
Integrate, this utility model has: installation weight is light, simple in structure, cost is low, windage is little, little to the air inlet of driving engine influence, is difficult for by the advantage of ice and snow foreign body obstruction.
Description of drawings:
Fig. 1 is the installation site scheme drawing of blade formula aircraft turbine engine guard.Blade (2) prolongs axle head through aero-engine to be fixed, and is installed in the admission port end of aero-engine (1).
Fig. 2 is the integrally-built scheme drawing of the utility model blade formula aircraft turbine engine guard blade part, the bending direction of blade will with the direction of rotation of aero-engine, be used to reduce windage.
Fig. 3 is the scheme drawing of the cross section structure of the utility model blade formula aircraft turbine engine guard blade, and blade is made streamline structure, is used to reduce windage, and adopts high-intensity material manufacture blade.
The specific embodiment:
Below in conjunction with description of drawings concrete structure of the present utility model.As shown in Figure 1, the blade formula aircraft turbine engine guard of the utility model prolongs axle by blade (2) and aircraft turbine engine and forms.Be installed in the inlet end of aircraft turbine engine (1); blade prolongs axle by aero-engine and drives rotation synchronously; after aero-engine starts; the turbine engine required air; before entering driving engine, at first to pass through this rotation blade; if be mingled with foreign matters such as flying bird in the inlet air, the blade of high speed revolution will smash and hit the foreign matter that may enter driving engine, thus the protection driving engine.Protection blade 6 will be done streamlining when actual production, blade is made bending, the bending direction of blade will with the direction of rotation of aero-engine, the above practice all is for reducing windage, because blade is high speed revolution under the drive of driving engine, when contacting, will produce very big impact, so require to be used for guaranteeing the aircraft flight safety with high-intensity material manufacture blade with foreign matter.Because this blade drives rotation synchronously by the aero-engine axle, requiring blade and driving engine to prolong the shaft connection place will have enough intensity.
Claims (3)
1, a kind of blade formula aircraft turbine engine guard is characterized in that, is installed in the blade (2) of the inlet end of aircraft turbine engine (1), and blade prolongs axle by aero-engine and drives rotation synchronously.
2, according to independent claims 1 described blade formula aircraft turbine engine guard, it is characterized in that the blade cross section is a streamline contour.
3, according to independent claims 1 described blade formula aircraft turbine engine guard, it is characterized in that blade is made bending, the bending direction of blade will with the direction of rotation of aero-engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201754406U CN201201716Y (en) | 2007-08-28 | 2007-08-28 | Protector for propeller type airplane turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201754406U CN201201716Y (en) | 2007-08-28 | 2007-08-28 | Protector for propeller type airplane turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201201716Y true CN201201716Y (en) | 2009-03-04 |
Family
ID=40424025
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201754406U Expired - Fee Related CN201201716Y (en) | 2007-08-28 | 2007-08-28 | Protector for propeller type airplane turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201201716Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101844622A (en) * | 2010-04-30 | 2010-09-29 | 厦门大学 | Anti-big bird hazard device for jet engine |
| WO2016095070A1 (en) * | 2014-12-19 | 2016-06-23 | 江阴古贝叶工业技术开发有限公司 | Protective apparatus for aircraft engine |
-
2007
- 2007-08-28 CN CNU2007201754406U patent/CN201201716Y/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101844622A (en) * | 2010-04-30 | 2010-09-29 | 厦门大学 | Anti-big bird hazard device for jet engine |
| WO2016095070A1 (en) * | 2014-12-19 | 2016-06-23 | 江阴古贝叶工业技术开发有限公司 | Protective apparatus for aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2014551B1 (en) | Device and method for protecting an aircraft component from collision with flying objects | |
| US8945255B2 (en) | Jet engine with deflector | |
| US3121545A (en) | Rotary deflector for aircraft engine intakes | |
| US10774744B2 (en) | Jet engine with deflector | |
| US20130327014A1 (en) | Devices and Methods to Optimize Aircraft Power Plant and Aircraft Operations | |
| US9090343B2 (en) | Rotor blade component cooling | |
| CN105814285A (en) | Composite fan inlet blade containment | |
| CN201201716Y (en) | Protector for propeller type airplane turbine engine | |
| US20100176599A1 (en) | Jet air recovery generator and jet blast deflector | |
| CN104608932A (en) | Aircraft engine protective device | |
| TWM469748U (en) | Complex automatic bird detection and expelling aircraft | |
| CN101885383A (en) | Aeroengine protective cover | |
| CN205469793U (en) | Arm is protected to wing for unmanned aerial vehicle | |
| CN202934453U (en) | Direct-coupled impeller head with impeller pre-accelerator | |
| US20150377131A1 (en) | System and Method for Preventing Objects From Entering the Intake of a Jet Engine | |
| US11338901B2 (en) | Nacelle for a boundary layer ingestion propulsor | |
| CN101844622A (en) | Anti-big bird hazard device for jet engine | |
| RU2168645C2 (en) | On-board system for protection of flying vehicle power plant against debris ingestion | |
| US20120216505A1 (en) | Aircraft | |
| US20230058777A1 (en) | Jet Engine Cover | |
| CN219008122U (en) | Anti-collision device for tail rotor of civil helicopter | |
| RU2305054C1 (en) | Air intake of aircraft equipped with turboprop engine | |
| US9689310B2 (en) | Airplane engine bird strike protection guard | |
| CN116723980A (en) | Aircraft cabin safety shield | |
| CN201431916Y (en) | Grinder protection device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090304 Termination date: 20090928 |