EXPLORATORY ANALYSIS OF PROPULSIVE LIFT ENGINES: PRELIMINARY ASSESSMENT

Authors
  1. Saravanamuttoo, H.I.H.
  2. Imray, M.D.
Corporate Authors
GasTOPS Ltd, Gloucester ONT (CAN);Chief of Research and Development, Ottawa ONT (CAN) Director Research and Development Air
Abstract
A preliminary assessment of four propulsive lift concepts for use with an Augmentor Wing transport was carried out. The augmentor wing application requires a continuous flow of relatively high pressure bleed air which dictates the use of a three stream engine. The most difficult design problem is the provision of a large quantity of bleed air during landing, with the forward thrust suppressed. Two concepts, the turboprop and the Unducted Fan, used ultra high by-pass ratio and it was found that the resulting small core flows made it extremely difficult to provide an adequate level of blowing thrust. Two turbofan variants, one with part span variable inlet guide vanes (VIGV) and the other a variable pitch fan, looked promising and worth further study. Neither of these engine types has any significant running experience and the required development programs would be substantial, but technology demonstrators could be based on modifications to existing engines.
Report Number
GTL-7-31.2-TR.1 — Technical Report
Date of publication
15 Sep 1986
Number of Pages
73
DSTKIM No
88-03534
CANDIS No
56753
Format(s):
Hardcopy;Originator's fiche received by DSIS

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