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

Clearance control system for separately expanding or contracting individual portions of an annular shroud

Patent 5281085 Issued on January 25, 1994. Estimated Expiration Date: Icon_subject January 25, 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

1678065

1678066

1734216

2402841

3029064

Thermal actuated valve for clearance control
Patent #: 4023731
Issued on: 05/17/1977
Inventor: Patterson

Clearance control for gas turbine engine
Patent #: 4069662
Issued on: 01/24/1978
Inventor: Redinger, Jr. ,   et al.

Seal clearance control system for a gas turbine
Patent #: 4213296
Issued on: 07/22/1980
Inventor: Schwarz

Compressor structure adapted for active clearance control
Patent #: 4268221
Issued on: 05/19/1981
Inventor: Monsarrat ,   et al.

Method and replacement member for repairing a gas turbine engine vane assembly
Patent #: 4305697
Issued on: 12/15/1981
Inventor: Cohen ,   et al.

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Inventors

Assignee

Application

No. 631512 filed on 12/21/1990

US Classes:

415/116, WITH DIVERSELY ORIENTED INLET OR ADDITIONAL INLET FOR DIVERSE FLUID (E.G., HEATING, COOLING OR MIXED WORKING FLUID, ETC.)415/173.2, Selectively adjustable415/178Working fluid on at least one side of heat exchange wall

Examiners

Primary: Look, Edward K.
Assistant: Verdier, Christopher

Attorney, Agent or Firm

Foreign Patent References

  • 188724 EP. 07/26/1986
  • 423025A1 EP. 04/26/1991
  • 0718703 FR 01/26/2013
  • 0054672 JP 04/26/1980
  • 1248198 GB. 09/26/1971
  • 2117842 GB 10/26/1983

International Class

F01D 009/00

Abstract

Improved operation can be achieved from an enhanced gas turbine engine having a segmented annular shroud which radially expands and contracts to match the expansion and contraction of engine rotor blades. The segmented annular shroud is supported by a structure which includes an annular ring having two radially outwardly extending flanges, and forward and aft annular segmented brackets which attach the segmented shroud to the forward and aft side of the ring respectively. In a preferred embodiment of the invention, two circumferentially extending separate and distinct air impingement manifolds surrounds each of the outwardly extending flanges. Each manifold is provided with a valve for controlling the amount and temperature of the airflow entering each manifold. The air from each manifold then impinges upon each of the outwardly extending flanges, thereby controlling the radial movement of the corresponding shroud segments and the associated clearances with the rotor blade tips. The use of separate and distinct manifolds and the corresponding values which regulate the amount and temperature of airflow to each manifold allows individual shroud portions to be separately expanded or contracted.

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