U.S. patents available from 1976 to present.
U.S. patent applications available from 2005 to present.

Gas turbine engine combustors

Patent 5187937 Issued on February 23, 1993. Estimated Expiration Date: Icon_subject February 19, 2011. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Patent References

2826039

2916878

3919840

Integral refilmer lip for floatwall panels
Patent #: 4653279
Issued on: 03/31/1987
Inventor: Reynolds

Combustion chamber liner insert Patent #: 4875339
Issued on: 10/24/1989
Inventor: Rasmussen, et al.

Inventors

Assignee

Application

No. 659353 filed on 02/19/1991

US Classes:

60/752, Combustor liner60/759Air scoop extends into air flowing outside liner

Examiners

Primary: Bertsch, Richard A.
Assistant: Thorpe, Timothy S.

Attorney, Agent or Firm

Foreign Patent References

  • 2636520 DE. 02/20/1978
  • 1331084 FR. 11/20/1963
  • 676473 GB 07/20/2013
  • 819065 GB. 08/20/2013
  • 943250 GB. 12/20/1963
  • 2017827 GB. 10/20/1979
  • 2113377 GB. 08/20/1983

International Class

F23R 003/04

Abstract

A gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet. The vortex generators can comprise an inwardly directed abrupt change of section between forward and rearward parts of the air inlets. The rearward section of the air inlets can have a configuration operative to reinforce the jet stabilizing effect of the vortex flow. The combustor exhibits improved uniformity of jet and crossflow mixing.

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