COLD-AIR PERFORMANCE OF FREE POWER TURBINE DESIGNED FOR 112-KILOWATT AUTOMOTIVE GAS-TURBINE ENGINE 3: EFFECT OF STATOR VANE END CLEARANCES ON PERFORMANCE

An experimental investigation of a free power turbine designed for a 112-kW, automotive, gas turbine engine was made to determine the penalty in performance due to the stator vane end clearances. Tests were made over a range of mean section stator vane angles from 26 deg to 50 deg (as measured from the plane of rotation) with the vane end clearances filled. These results were compared with test results of the same turbine with vane end clearances open. At design equivalent values of rotative speed and pressure ratio and at a vane angle of 35 deg, the mass flow with the vane and clearances filled was about 8 percent lower than mass flow with vane end clearances open. The decrease in mass flow was mitigated by increasing the vane angle. With the vane end clearances filled, there was about a 66 percent reduction in mass flow when the vane angle was decreased from 40 deg to 26 deg. For the same decrease in vane angle the stator throat area decreased by about 50 percent. This result indicates that the rotor losses were increasing with decreasing vane angle.

  • Corporate Authors:

    Department of the Navy

    The Pentagon
    Washington, DC  United States  20350
  • Authors:
    • Kofskey, M G
    • Mclallin, K L
  • Publication Date: 1978-12

Media Info

  • Pagination: 41 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00191209
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-78956, DOE/NASA/1011-78/29
  • Contract Numbers: EC-77-A-31-1011
  • Files: TRIS
  • Created Date: May 11 1979 12:00AM