A methodology for quantifying relative life/performance trades during the conceptual design phase of gas turbine engine development is presented. These trades, which have not been quantified in past conceptual efforts, will identify the sensitivity of turbine engine performance and weight due to changes in life. This methodology, developed under Air Force (AFWAL) sponsorship, will aid in balancing performance and life goals at preliminary design, resulting ultimately in improved gas turbine engine designs. A computer-aided design system has been developed and demonstrated. Selected fan, compressor, high pressure turbine and low pressure turbine blade, blade/disk attachment and disk designs were generated for an advanced turbofan engine. A composite steady-state and cyclic mission usage was specified at several conditions in the flight envelope. Component life and other design criteria were addressed for the range of stresses and design-limiting modes of the various components. (Wassmann)
Engine life and usage methodologies for conceptual design
Methoden fuer die Lebensdauer- und Betriebsauslegung von Triebwerken in der Planung
AIAA-Papers ; 1-8
1981
8 Seiten, 21 Bilder, 3 Quellen
Conference paper
English
Engine life methodologies for conceptual design
AIAA | 1981
Optimization Methodologies in Conceptual Design
AIAA | 2002
|Conceptual Design Methodologies for Flyingboats and Floatplanes
British Library Conference Proceedings | 1996
|