COMPUTER MODEL OF A VARIABLE PITCH FAN PROPULSIVE LIFT ENGINE: THERMODYNAMIC ANALYSIS AND SYSTEM DESIGN

Authors
  1. Imray, M.D.
Corporate Authors
GasTOPS Ltd, Gloucester ONT (CAN);Chief of Research and Development, Ottawa ONT (CAN) Director Research and Development Air
Abstract
The Department of National Defence (DND) is investigating the application of augmentor wing (AW) technology to a future short take-off and landing (STOL) transport aircraft. Part of this exercise includes an assessment of the power-plants proposed for the AW application. GasTOPS Ltd. was tasked to perform an independent evaluation of the proposed configurations followed by an in-depth analysis of the most favourable concept(s). A preliminary assessment has concluded that one of the more promising concepts is the variable pitch fan engine. This document provides a description of the thermodynamic analysis and system design for a component based matching program used to model the engine.
Report Number
GTL-7-31.3-TR.5 — Technical Report
Date of publication
15 Dec 1987
Number of Pages
74
DSTKIM No
88-03529
CANDIS No
56748
Format(s):
Hardcopy;Originator's fiche received by DSIS

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