RU2010136592A - AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER - Google Patents
AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER Download PDFInfo
- Publication number
- RU2010136592A RU2010136592A RU2010136592/11A RU2010136592A RU2010136592A RU 2010136592 A RU2010136592 A RU 2010136592A RU 2010136592/11 A RU2010136592/11 A RU 2010136592/11A RU 2010136592 A RU2010136592 A RU 2010136592A RU 2010136592 A RU2010136592 A RU 2010136592A
- Authority
- RU
- Russia
- Prior art keywords
- propeller
- blade
- compressor
- jet
- blades
- Prior art date
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Авиационный бестурбинный компрессорный воздушно-реактивный двигатель - сверхзвуковой реактивный пропеллер содержит устройство передачи механической энергии движения от реактивного сопла двигателя к его вращающемуся валу, выполненное в виде сверхзвукового реактивного пропеллера, в котором лопасти расположены под углом стреловидности к вектору окружной скорости сечения лопасти, где указанный угол - это угол между передней кромкой лопасти и плоскостью, перпендикулярной вектору окружной скорости сечения лопасти, камера сгорания топлива с реактивным соплом установлена на конце стреловидной лопасти, а воздушный компрессор состоит из расположенного в области втулки пропеллера компрессора предварительного сжатия воздуха, снабженного приводом, и центробежного компрессора высокого давления, выполненного в виде полых лопастей самого пропеллера, причем выходное отверстие компрессора предварительного сжатия воздуха сквозь полые лопасти пропеллера связано со входным отверстием камеры сгорания топлива. An aircraft turbine-free compressor jet engine — a supersonic jet propeller — comprises a device for transmitting mechanical energy of motion from the jet nozzle of the engine to its rotating shaft, made in the form of a supersonic jet propeller, in which the blades are located at an angle of sweep to the circumferential velocity of the blade section, where the specified angle is the angle between the leading edge of the blade and the plane perpendicular to the vector of the peripheral velocity of the section of the blade, the combustion chamber of the fuel An air nozzle with a jet nozzle is installed at the end of the swept blade, and the air compressor consists of a pre-compressed air compressor equipped with a drive located in the area of the propeller hub and a high-pressure centrifugal compressor made in the form of hollow blades of the propeller itself, and the outlet of the air pre-compressor through The hollow propeller blades are connected to the inlet of the fuel combustion chamber.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010136592/11A RU2010136592A (en) | 2010-08-31 | 2010-08-31 | AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010136592/11A RU2010136592A (en) | 2010-08-31 | 2010-08-31 | AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| RU2010136592A true RU2010136592A (en) | 2012-03-10 |
Family
ID=46028813
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2010136592/11A RU2010136592A (en) | 2010-08-31 | 2010-08-31 | AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2010136592A (en) |
-
2010
- 2010-08-31 RU RU2010136592/11A patent/RU2010136592A/en not_active Application Discontinuation
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11988099B2 (en) | Unducted thrust producing system architecture | |
| US10399664B2 (en) | Immersed core flow inlet between rotor blade and stator vane for an unducted fan gas turbine | |
| CN104937236B (en) | Turbine rotor blade | |
| KR101891853B1 (en) | Centrifugal Compressor Impeller | |
| RU2014139584A (en) | DESIGN OF A REDUCED GAS TURBINE ENGINE, ENSURING AN INCREASED EFFICIENCY | |
| CN106089799B (en) | Compression rotor based on compression technology of air inlet passage of scramjet engine | |
| RU2010136592A (en) | AIRCRAFT COMPRESSOR AIR-REACTIVE ENGINE - SUPERSONIC REACTIVE PROPELLER | |
| RU2007138828A (en) | Flying apparatus "Flying Saucer" | |
| RU2495269C2 (en) | Compressor air breather | |
| RU2508468C2 (en) | Wind motor | |
| RU2010144228A (en) | SCREW AIR-REACTIVE ENGINE (VK WFD) | |
| CN205078365U (en) | Jet engine | |
| RU2382896C2 (en) | Device to transfer mechanical power from internal combustion engine to thermal electric power station generator | |
| CN102900471A (en) | Efficient low-resistant structural or efficient energy-gathered structural or efficient engine | |
| KR20110083363A (en) | Impeller and compressor | |
| CN102192045A (en) | Stamping type rotor fan engine | |
| RU2338666C2 (en) | Shesterenko device for ejector aircraft speed-up | |
| RU2551548C1 (en) | Aircraft | |
| RU2008100496A (en) | BIOTATIVE VENTILATION FAN AIRCRAFT ENGINE | |
| RU2010111609A (en) | JET HELICOPTER MOTOR | |
| RU2011128210A (en) | Flying apparatus "Flying Saucer" | |
| US9810145B1 (en) | Ducted impeller | |
| CN112282964A (en) | High-thrust engine for aircraft | |
| RU2008115651A (en) | GAS TURBOCHEMBER AND TURBO-SCREW GAS TURBINE ENGINE | |
| RU2354584C2 (en) | Lifting screw |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FA93 | Acknowledgement of application withdrawn (no request for examination) |
Effective date: 20130902 |