Title:
SUPERSONIC AIRPLANE ENGINE CONFIGURATION
Document Type and Number:
WIPO Patent Application WO1982000048
Kind Code:
A1
Abstract:
A supersonic airplane has a fuselage (20), wings (22) and (24), a vertical stabilizer (34 - 38), a canard (30) and (32) and a pair of turbine engines (44, 46 or 70) mounted in the fuselage (20). Each engine (44, 46 or 70) is of relatively simple de-sign with a fixed inlet, a compressor (80 - 82) and a turbine (84) with a single drive shaft (76) interconnecting the turbine (84) and compressor (80). The engine (44, 46 or 70) can employ either fixed or variable exhaust nozzle geometry (75) depending on whether an afterburner is installed. The engine (70) is point designed to provide maximum design thrust at a given intermediate throttle setting when the airplane is being propelled by the engine (70) at a predetermined supersonic cruise Mach number. Maximum allowable thrust at speeds below the predetermined cruise Mach number is achieved without variable geometry air inlets by maintaining the corrected airflow through the engine (70) at a substantially constant value equivalent to the corrected airflow at the predetermined supersonic cruise Mach number. The engine (70) corrected airflow is maintained at a constant value by monitoring an engine operating parameter indicative of corrected airflow and adjusting the fuel flow to the engine (70) to reduce the actual speed of the compressor (80 - 82) and turbine (84).
Inventors:
BROWN R (US)
Application Number:
PCT/US1980/000786
Publication Date:
January 07, 1982
Filing Date:
June 23, 1980
Export Citation:
Assignee:
BOEING CO (US)
International Classes:
B64C30/00; F02C9/44; (IPC1-7): F02K3/00
Foreign References:
| US2850871A | 1958-09-09 | |||
| US2971328A | 1961-02-14 | |||
| US2982496A | 1961-05-02 | |||
| US3067577A | 1962-12-11 | |||
| US3164202A | 1965-01-05 | |||
| US3181817A | 1965-05-04 | |||
| US3188022A | 1965-06-08 | |||
| US3680816A | 1972-08-01 | |||
| US3813063A | 1974-05-28 | |||
| US3854287A | 1974-12-17 | |||
| US3866416A | 1975-02-18 | |||
| US3129563A | 1964-04-21 |
Other References:
See also references of EP 0054555A4
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