Design of High Heat Release Slinger Combustor with Rapid Acceleration Requirement Teledyne CAE

Format:

Conference/Event

Author/Creator:

Rogo, Casimir, author.

Conference Name:

1974 Automotive Engineering Congress and Exposition (1974-02-25 : Detroit, Michigan, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1974

Summary:

Reliable turbojet engine ignition and rapid acceleration at high combustor heat release rates have recently gained in importance for drone and missile applications. These requirements are imposed due to the necessity to minimize engine size and booster needs. Because of the mission and flight envelope, the combustor must also be capable of high-altitude variable Mach number and windmill starts. Design and development of a 10 lb/s airflow combustor delivering in excess of 12 106 Btu/h-ft3-atm (1.22 kW/m3 Pa) is described. Pyrotechnic devices are used for ignition and acceleration. Optimized fuel scheduling combined with efficient combustor and fuel slinger characteristics have demonstrated engine start and acceleration to maximum power in less than 5 s at sea-level conditions

Notes:

Vendor supplied data

Publisher Number:

740167

Access Restriction:

Restricted for use by site license