Inlet flow-field measurements of a transonic compressor rotor prior to and during steam-induced rotating stall
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Authors
Payne, Thomas A.
Subjects
Advisors
Hobson, Garth V.
Date of Issue
2005-12
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Steam leakage from an aircraft carrier catapult is sometimes ingested by the aircraft's engines upon launch which may induce compressor stall. Investigation of the phenomenon known as a "pop stall" is of particular importance as the Navy prepares to field the F35C, the aircraft carrier variant of the joint strike fighter. The single engine design of the F-35C makes this aircraft particularly susceptible to steam-induced stall during catapult launch. The present project examined compressor stall and included steady-state as well as transient measurements in the inlet of a transonic compressor prior to and during a steaminduced stall. Hotwire measurements of the inlet flow field were taken to determine an inlet turbulence intensity of 2-3% during both subsonic as well as transonic compressor operation. A 95% speed line was established from data taken from open throttle to near stall. Hot-film and Kulite pressure data taken near stall showed the existence of a stall precursor which appeared near half rotor speed. Steam was injected into the inlet; however the initial method added mass to the system and did not induce a stall. A decrease in the amplitude of the pressure trace was observed however. A stall was induced by steam ingestion ahead of the existing inlet throttle, with upstream transient measurements taken using both hot-film and Kulite pressure transducers.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Astronautical Engineering (MAE)
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
xiv, 71 p. : col. ill. ;
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Approved for public release; distribution is unlimited.
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.