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

Vane rotator assembly for a gas turbine engine

Patent 4130375 Issued on December 19, 1978. Estimated Expiration Date: Icon_subject October 11, 1997. 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

2671634

3089679

3538579

3685921

3788763

High ratio actuation linkage
Patent #: 3990809
Issued on: 11/09/1976
Inventor: Young ,   et al.

Variable turbomachine stator Patent #: 3999883
Issued on: 12/28/1976
Inventor: Nordenson

Inventor

Assignee

Application

No. 05/840898 filed on 10/11/1977

US Classes:

415/161, And fixed vane415/162, Plural, selectively adjustable vane sets415/191, Vanes74/96Oscillating to oscillating

Examiners

Primary: Croyle, Carlton R.
Assistant: Holland, Donald S.

Attorney, Agent or Firm

International Classes

F01D 17/00 (20060101)
F01D 17/16 (20060101)

Foreign Application Priority Data

1975-10-14 CA

Abstract

This invention relates to a method of moving a set of adjustable trailing vanes in a gas turbine engine of the "split-shaft" type. The vanes are moved by an adjusting ring which is made to completely encircle the casing of the turbine and connect to each vane by means of a rotator assembly. Provision is made to allow for connection of the turbine casing so that the binding or flexing of the adjustor ring assembly during thermal cycling is avoided. A series of pitman arms are pivotally interconnected between the adjustor ring assembly and each vane rotator assembly. The vane rotator assembly is provided to intercouple the adjustor ring assembly to each pivoting vane while at the same time providing some radial flexibility for the vane itself to prevent binding of the blade and actuator during thermal cycling. Provision is also made to bias each pivoting vane in the particular direction in the turbine during the operation of the turbine.

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