{"id":{"repo_id":"nps","oai_identifier":"oai:calhoun.nps.edu:10945/1751"},"canonical_url":"https://search.dev.ndltd.org/etd/nps/oai:calhoun.nps.edu:10945/1751","repository":{"repo_id":"nps","name":"Naval Postgraduate School","base_url":"https://calhoun.nps.edu/server/oai/request"},"display":{"title":"Inlet flow-field measurements of a transonic compressor rotor prior to and during steam-induced rotating stall","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.","abstract_html":"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.","abstract_has_math":false,"creators":["Payne, Thomas A."],"institution":"Monterey, CA; Naval Postgraduate School","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Mechanical and Aerospace Engineering (MAE)","school":null,"contributors":[],"advisors":["Hobson, Garth V."],"committee_chairs":[],"committee_members":[],"year":2005,"date_issued":"2005-12","date_published":"2005-12","updated_at":"2026-07-27T20:26:05Z","subjects":[],"languages":[],"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."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/10945/1751","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Hobson, Garth V."]},{"key":"dc:contributor.department","label":"Department","values":["Mechanical and Aerospace Engineering (MAE)"]},{"key":"dc:creator","label":"Author","values":["Payne, Thomas A."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2012-03-14T17:32:58Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2012-03-14T17:32:58Z"]},{"key":"dc:date.issued","label":"Date","values":["2005-12"]},{"key":"dc:publisher","label":"Institution","values":["Monterey, CA; Naval Postgraduate School"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:rights","label":"Dc Rights","values":["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."]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["https://hdl.handle.net/10945/1751"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["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."]},{"key":"dc:title","label":"Title","values":["Inlet flow-field measurements of a transonic compressor rotor prior to and during steam-induced rotating stall"]}]}],"canonical_facts":{"dc:contributor.advisor":["Hobson, Garth V."],"dc:contributor.department":["Mechanical and Aerospace Engineering (MAE)"],"dc:creator":["Payne, Thomas A."],"dc:date.accessioned":["2012-03-14T17:32:58Z"],"dc:date.available":["2012-03-14T17:32:58Z"],"dc:date.issued":["2005-12"],"dc:description.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."],"dc:identifier.uri":["https://hdl.handle.net/10945/1751"],"dc:publisher":["Monterey, CA; Naval Postgraduate School"],"dc: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."],"dc:title":["Inlet flow-field measurements of a transonic compressor rotor prior to and during steam-induced rotating stall"],"dc:type":["Thesis"]},"updated_at":"2026-07-27T20:26:05Z"}