Variable vane non-linear schedule for a gas turbine engine

• US 5,190,439 A
• Filed: 07/15/1991
• Issued: 03/02/1993
• Est. Priority Date: 07/15/1991
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Das, Ranjan
• Primary Examiner(s): Kwon, John T.
• Assistant Examiner(s): Lee, Michael S.
• Application Number:
  US07/731,213
• Time in Patent Office: 596 Days
• Field of Search: 415/17, 415/33, 415/149.4, 415/160, 415/162, 415/161, 416/157 B, 416/168 A
• US Class Current: 415/149.4
• CPC Class Codes: F01D 17/16 by means of nozzle vanes
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps

Abstract

A method and apparatus for adjusting the angle of variable angle inlet guide vanes provides a non-linear adjustment schedule for a selected vane row as compared to the adjustment schedule for the IGV vane row. The non-linear schedule is conveniently achieved by providing a modified adjustment linkage utilizing a bell crank. The non-linear schedule provides improved engine stall margin at low engine speeds.

Claims

1. In a method for operating a gas turbine engine having a compressor section with a plurality of rows of variable angle stator vanes, including a variable angle IGV vane row, wherein the angle of said IGV vane row is changed as a function of engine speed, and the angle of at least one other vane row is changed as a linear function of the angle of said IGV vane row, the improvement wherein the angle of a third vance row is varied as a non-linear function of the angle of said IGV vane row, said non-linear function being approximately linear at higher engine speeds and having greater than said linear variation at engine start and idle speeds and wherein said engine has a fourth row of stator vanes following said third vane row, and wherein the angle of said forth row is maintained constant for all engine speeds.

2. Apparatus for adjusting the compressor stator vane angles in a gas turbine engine having a plurality of compressor stator vane rows, comprising:

a pump handle , having one end pivotably mounted to a stationary part of said engine, and having at least one link member connected directly thereto for adjusting the vane angle of a first of said inlet vane rows;

means for selectively pivoting said pump handle about said pivotable mount in response to an engine operating condition; and

a bell crank having a first pivot point mounted to a stationary part of said engine, a second pivot point mounted by a bell crank pivot link to said pump handle and a third pivot point connected to another link member for adjusting the vane angle of another of said inlet vane rows; and

whereby said pivoting of said pump handle causes adjustment of the angle of said other of said vane rows in a manner that is non-linearly related to the adjustment of said angle of said first inlet vane row.

3. Apparatus as specified in claim 2 wherein said pump handle has an additional link member connected directly thereto for adjusting the vane angle of a second of said inlet guide vane rows.