Design objectives and features of advanced turbofan engine on order for Lockheed 1011 three-engined transport aircraft; engine is also offered for 200-seat twin engine transports; specification and performance data; arrangement of engine is as follows -- single stage front fan, without inlet guide vanes, is driven from three-stage low-pressure turbine, system being mechanically independent of gas generator; gas generator consists of seven stage intermediate pressure (i.p.) compressor driven by single stage uncooled i.p. turbine, and six stage h-p compressor driven by single stage air cooled h-p turbine; combustion chamber is annular; installation details, engine test program and component testing; combustion and engine control system; maintainability aspects. (See also Aircraft Eng v 40 n 4 Apr 1968 p 22-4, 26)
Rolls-Royce RB.211 three shaft turbofan
Flight
Flight International ; 92 , n 3061
1967
3 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Rolls-Royce three shaft turbofan engine
Engineering Index Backfile | 1968
|The Rolls-Royce Three Shaft Turbofan Engine
Emerald Group Publishing | 1968
|The Rolls-Royce three-shaft turbofan engine
AIAA | 1967
|Rolls-Royce RB.211 three shaft turbofan
Engineering Index Backfile | 1968
The Rolls-Royce RB.211 Three Shaft Turbofan
Emerald Group Publishing | 1968