FIELD: engines and pumps.
SUBSTANCE: bypass turbojet comprises mid case including inner wall composed of solid of revolution to confine primary airflow duct from outside and air bleeders. High-pressure compressor outer case is secured at downstream end. Air bleeders are arranged in said high-pressure compressor channel and connected at its outlet with re-injectors of air into high-pressure compressor upstream section. Air bleeders are communicated with air re-injectors via circular manifold covering mid case including inner wall composed of solid of revolution upstream of high-pressure compressor. They are located radially between mid case including inner wall composed of solid of revolution to confine turbine secondary airflow duct from inside.
EFFECT: simplified design at normal weight and length of gas turbine.
13 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE ENGINE COMBUSTION CHAMBER WALL VENTILATION SYSTEM AND GAS TURBINE ENGINE WITH SAID SYSTEM | 2007 |
|
RU2446296C2 |
| HIGH-EFFICIENCY THERMAL ENGINE | 2006 |
|
RU2380557C2 |
| SYSTEM TO COOL CENTRIFUGAL COMPRESSOR CROWN | 2007 |
|
RU2433308C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| GAS TURBINE ENGINE HIGH-PRESSURE TURBINE VENTILATION | 2009 |
|
RU2504662C2 |
| INJECTION SYSTEM OF AIR MIXED WITH FUEL TO COMBUSTION CHAMBER OF GAS TURBINE ENGINE | 2008 |
|
RU2478878C2 |
| GAS TURBINE ENGINE, FOR EXAMPLE AIRCRAFT TURBOJET ENGINE | 2005 |
|
RU2373402C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| METHOD OF CIRCULATING AIR IN TURBINE COMPRESSOR, COMPRESSOR EXPLOITING THIS METHOD, COMPRESSOR STAGE OF AFORESAID DESIGN AND AIRCRAFT ENGINE INCORPORATING SAID COMPRESSOR | 2005 |
|
RU2370674C2 |
| GAS TURBINE ENGINE COMPRESSOR AIR BLEEDER | 2008 |
|
RU2486374C2 |
