CN106286008A - High air compression ratio aero-engine - Google Patents
High air compression ratio aero-engine Download PDFInfo
- Publication number
- CN106286008A CN106286008A CN201510381055.6A CN201510381055A CN106286008A CN 106286008 A CN106286008 A CN 106286008A CN 201510381055 A CN201510381055 A CN 201510381055A CN 106286008 A CN106286008 A CN 106286008A
- Authority
- CN
- China
- Prior art keywords
- drive
- hydraulic drive
- engine
- hydraulic
- variator
- 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
Links
Abstract
Technical field this be high air compression ratio aero-engine, various Aircraft requirements can be met.Main feature and purposes make the rotary shaft of turbine rotate by aero-engine self jet effect, and make driving force be sent to hydraulic drive portion (A) (being become hydraulic drive from through-drive), it is connected transmission with variator by hydraulic drive portion (B) (being converted into through-drive by hydraulic drive) and realizes rotating speed by variator and promote.The series connection snap-in gear of speed change gear, makes the rotary shaft of engine compressor and the rotating speed of fan accelerate or become big, and causes the air compression of compressor more fiercely, provides bigger air capacity to electromotor self.And making the cooling degree of combustor bigger, the air enabling combustor to inject more fuel and q.s fully burns and produces and more powerful fires stamping press.
Description
Technical field
The aeroengine thrust designed as accompanying drawing is higher.
Background technology
This is a kind of novel aero-engine, can meet various Aircraft requirements.
1, engine total is constituted
A, composition: various reaction turbines or fan aero-engine and speed change gear.
B, each several part physique structure feature and action character:
As it can be seen, be mounted with a speed change gear outside electromotor, this speed change gear is integrated upgrade version, multiple speed change gear combine, and represents each speed change gear respectively with solid line and dotted line in figure.From with hydraulic drive portion (A) device of electromotor jet plane rotary shaft gear snap-in from the beginning of, by with hydraulic pressure outlet pipe to hydraulic drive portion (B), it is transferred to the power transmission shaft of snap-in between engine compressor rotary shaft gear again by speed changer, finally makes compressor rotary shaft rotating speed obtain and improve to the limit.
2, cardinal principle effect
The rotary shaft being made turbine by aero-engine self jet effect is rotated, and make driving force be sent to hydraulic drive portion (A) (being become hydraulic drive from through-drive), it is connected transmission with variator by hydraulic drive portion (B) (being converted into through-drive by hydraulic drive) and realizes rotating speed by variator and promote.The series connection snap-in gear of speed change gear, makes the rotary shaft of engine compressor and the rotating speed of fan accelerate or become big, and causes the air compression of compressor more fiercely, provides bigger air capacity to electromotor self.And making the cooling degree of combustor bigger, the air enabling combustor to inject more fuel and q.s fully burns and produces and more powerful fires stamping press.
Accompanying drawing explanation
Accompanying drawing is " aero-engine speed change gear partial schematic diagram ".
Claims (5)
1. make the rotary shaft of turbine rotate by aero-engine self jet effect, and make driving force be sent to hydraulic drive portion (A)
(being become hydraulic drive from through-drive), by hydraulic drive portion (B) (being converted into through-drive by hydraulic drive) with variator even
Connect transmission and realize rotating speed lifting by variator.The series connection snap-in gear of speed change gear, makes the rotation of engine compressor
The rotating speed of axle and fan accelerates or becomes big, and causes the air compression of compressor more fiercely, provides bigger to electromotor self
Air capacity.
2. driving force is sent to pump type hydraulic driving section (A) (being become hydraulic drive from through-drive), liquid by alphabet sequence c, d,
E, f form hydraulic drive order, and pump type hydraulic driving section (B) (being converted into through-drive by hydraulic drive) is to pass through hydraulic drive
Sequentially c, d, e, f formation hydraulic transmission principle completes.
3. (passed by the head end of the power transmission shaft of hydraulic drive portion (B) (being converted into through-drive by hydraulic drive) with variator/change speed gear box
Moving axis) connect, and realize speed change by variator and make transmission rotating speed become big.
4. with dividing line inside and outside aero-engine as boundary, by the such as through-drive, hydraulic drive of the various kinds of drive, linked transmission etc. (as
Figure), realize variable speed design at external engine.
5. such as figure shaft type in various manners or linked transmission, by electromotor jet turbine axle and external engine variable speed design phase snap-in or
Connect and external engine variable speed design is calmed the anger with electromotor portion's rotary shaft snap-in or connect, and finally realize compressor portion fan
Speed change.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510381055.6A CN106286008A (en) | 2015-06-24 | 2015-06-24 | High air compression ratio aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510381055.6A CN106286008A (en) | 2015-06-24 | 2015-06-24 | High air compression ratio aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106286008A true CN106286008A (en) | 2017-01-04 |
Family
ID=57651255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510381055.6A Pending CN106286008A (en) | 2015-06-24 | 2015-06-24 | High air compression ratio aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106286008A (en) |
-
2015
- 2015-06-24 CN CN201510381055.6A patent/CN106286008A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2964921B1 (en) | Multi-shaft gas turbine engine | |
| EP2728140A3 (en) | Booster assembly for gas turbine engine comprising a gearing | |
| CN107725476B (en) | A kind of adjustable hydraulic propeller of blade-section | |
| RU2008141617A (en) | IMPROVEMENT OF HELICOPTER AIRCRAFT EQUIPPED WITH GAS-TURBINE ENGINES | |
| CN102900542A (en) | Motor-generator and prime mover gearing assembly | |
| US11346357B2 (en) | Individual axis driven three stage counter rotating axial flow pump | |
| CN106195136B (en) | A kind of gear-driven fan (GTF) motor gear transmission device | |
| CN103303451A (en) | Hydraulically-driven full-vector water-jet propulsor spout | |
| CN108518289A (en) | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan | |
| JP2016041931A (en) | Mechanical drive architectures with mono-type low-loss bearings and low-density materials | |
| DE102015014868A1 (en) | Air-jet engine with three-stage rotary piston engine with continuous combustion process. | |
| CN103953395A (en) | Hydrodynamic force machine with rotating wheel slewing mechanism | |
| RU2013101080A (en) | GAS-TURBINE ENGINE PILON ASSEMBLY AND GAS-TURBINE ENGINE SYSTEM | |
| JP2016041936A (en) | Mechanical drive architectures with hybrid-type low-loss bearings and low-density materials | |
| CN106286008A (en) | High air compression ratio aero-engine | |
| US20160201682A1 (en) | Split axial-centrifugal compressor | |
| CN2924153Y (en) | Hydraulic transmission | |
| CN105179021A (en) | Counter-rotating impeller mechanism and device comprising same | |
| CN105480407A (en) | Blade end spraying and pushing technology for rotary blades | |
| CN105443270A (en) | Novel aviation turbofan engine | |
| CN112762024B (en) | Double-shaft bidirectional-transmission spiral axial-flow oil-gas mixed transmission pump | |
| CN106907180A (en) | Contra-rotating rotor mechanism | |
| CN205707340U (en) | A kind of helicopter reductor | |
| RU2379523C2 (en) | Aircraft propfan engine | |
| CN109653867A (en) | A kind of fan coupler gear case |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| DD01 | Delivery of document by public notice | ||
| DD01 | Delivery of document by public notice |
Addressee: Sun Guoli Document name: Notification that Application Deemed to be Withdrawn |
|
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170104 |