Publication Date:
2019-07-13
Description:
Candidate external vaporizer designs for an aircraft gas turbine engine are evaluated with respect to fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements, safety, and maintenance. The selected concept is shown to offer potential gains in engine performance in terms of reduced specific fuel consumption and improved engine thrust/weight ratio. The thrust/weight improvement can be traded against vaporization system weight.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
ASME PAPER 81-GT-158
,
Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
Format:
text
Permalink