Accession Number:

AD0739922

Title:

Advanced Seal Technology.

Descriptive Note:

Final rept. 30 Apr-30 Nov 71,

Corporate Author:

PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN

Personal Author(s):

Report Date:

1972-02-01

Pagination or Media Count:

10.0

Abstract:

The limitations of present aircraft gas turbine engine dynamic seal technology were reviewed and the effect of gas path seal losses on four representative current and advanced transport and fighter aircraft engine cycles was established. Four key seal locations were identified high-pressure compressor blade tip seal cantilevered compressor stator tip seal high-pressure turbine blade tip seal and turbine interstage seal. An evaluation of a variety of seal concepts and preliminary designs yielded four candidate seal concepts for operation in environments up to 1500F compressor discharge temperature, 3200F turbine inlet temperature, 600 psi maximum pressure and rotor speeds consistent with advanced engine cycles. Final design layouts were prepared for the two most promising of these seals a free-floating compositeabradable compressor blade tip seal and a high-pressure turbine blade tip seal using integrally cost extensions of the second-stage vane platform as first-and second-stage blade tip rubstrips. Finally, recommendations for experimental evaluation of the two final seal designs were developed. Author

Subject Categories:

  • Adhesives, Seals and Binders
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE