rdf-syntax-grammar
mods:
  schema location: http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
  title info:
    title: Jet impingement heat transfer in rotating coolant passages
  name:
    name part: Parsons, James Auner.
    role:
      role term: creator
  type of resource: text
  genre: bibliography
  origin info:
    place:
      place term: xx
    date issued: 1995
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: print
    extent: x, 96 leaves : illustrations ; 28 cm.
  abstract: In gas turbine engines, increasing turbine inlet temperature increases engine thermal efficiency but also increases the amount of heat transferred to the turbine blades. To achieve reasonable turbine blade durability goals, the blades are cooled with air extracted from the compressor but at a penalty to the efficiency. Advanced turbine blade design employs jet impingement cooling for internal blade surfaces. Using stationary models, many tests have optimized impingement designs for turbine operating conditions. However, rotation of turbine blades introduces centrifugal and Coriolis forces on the coolant inside the blades. These forces alter coolant motion and thus heat transfer for internal blade surfaces. Therefore, tests have been conducted to obtain local heat transfer coefficients and the coolant flow distribution for rotating channels with impingement cooling by arrays of circular jets. Additional stationary tests serve for a baseline and for comparison with other investigations. Results of this study are important to turbine rotor blade coolant passage design. Jet flow direction was in the direction of rotation in one channel and opposite to the rotation direction in the other channel. The air jets impinged normally on smooth target walls. Heat transfer and flow distribution results are presented for these two target walls. Two flow exit configurations were studied: flow exited both channels in a single direction, radially outward, creating cross flow on jets at larger radii, and flow exited through extraction orifices in each target wall creating little cross flow on other jets. Jet rotation number, EIDN,, was varied from 0.0 to 0.0055 and the isolated effects of jet Reynolds number (2500 to 10,000), rotation speed (0, 400 and 800 rpm) and heated wall-to- coolant temperature difference (AT = 11, 28 and 45K) were measured. Also the number of extraction orifices was reduced by 50%.
  note: by James Auner Parsons.
  note: "Major Subject: Mechanical Engineering".
  note: Vita.
  note: Issued also on microfiche from University Microfilms Inc.
  note: Ph. D. Texas A&M University 1995.
  note: Includes bibliographical references.
  subject:
    topic: Major mechanical engineering
  identifier: https://hdl.handle.net/1969.1/DISSERTATIONS-1575860
  related item:
    location:
      url: https://hdl.handle.net/1969.1/DISSERTATIONS-1575860
  record info:
    record content source: TXA
    record creation date: 961010
    record change date: 20220103134956.0
    record identifier: in00001322075