A Probabilistic Evaluation of Turbofan Engine Cycle Parameters for a Mach 1.8 Interceptor Aircraft Aerospace Systems Design Laboratory, Georgia Institute of Technology

Format:

Conference/Event

Author/Creator:

Lin, Tsung Po, author.

Conference Name:

World Aviation Congress & Exposition (2003-09-08 : Montreal, Canada)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2003

Summary:

A supersonic engine for a high Mach interceptor mission is modeled, and the requirements for the engine at different flight conditions are discussed. These include low fuel consumption at a non-afterburning supersonic dash Mach number for interception, and high thrust, both afterburning and non-afterburning, at a high subsonic Mach number for combat engagement. In addition, the engine should have low frontal area and low weight for a given sea level thrust rating. For the design point, the sea level static, standard day non-afterburning thrust is fixed at 20,000 lbs. The primary independent parameters varied in the study are fan pressure ratio, overall pressure ratio, turbine inlet temperature, throttle ratio, and extraction ratio.A design of experiments (DoE) is set up to vary the independent parameters to produce a meta-model for engine performance, geometry and weight. A simulation environment is established using this meta-model, and a probabilistic analysis is conducted to establish the probability of achieving specified values for performance, weight and frontal area

Notes:

Vendor supplied data

Publisher Number:

2003-01-3056

Access Restriction:

Restricted for use by site license