Gas turbine engine stator vane asymmetry

Patent metadata

Field	Value
Publication number	US-2016160665-A1
Application number	US-201514713103-A
Country	US
Kind code	A1
Filing date	May 15, 2015
Priority date	May 23, 2014
Publication date	Jun 9, 2016
Grant date	—

Abstract

A gas turbine engine includes an array of airfoils that include first and second segments. The first segment includes a first number of airfoils that are circumferentially spaced from one another a first angular spacing. The second segment includes a second number of airfoils that are circumferentially spaced from one another a second angular spacing. A sum of the first and second number of airfoils corresponds to a total number of airfoils in the array. The first angular spacing is based upon a first effective number of total airfoils in the array that is different than the total number of airfoils.

First claim

What is claimed is:

1 . A gas turbine engine comprising:
an array of airfoils including first and second segments, the first segment including a first number of airfoils circumferentially spaced from one another a first angular spacing, the second segment including a second number of airfoils circumferentially spaced from one another a second angular spacing, a sum of the first and second number of airfoils corresponding to a total number of airfoils in the array, the first angular spacing based upon a first effective number of total airfoils in the array that is different than the total number of airfoils.

2 . The gas turbine engine according to claim 1 , wherein the array includes two arcuate segments that are each approximately 180°.

3 . The gas turbine engine according to claim 1 , wherein the first effective number of total airfoils in the array is a fractional number.

4 . The gas turbine engine according to claim 3 , wherein the first angular spacing is 360° divided by the first effective number of total airfoils in the array.

5 . The gas turbine engine according to claim 4 , wherein the first effective number of total airfoils in the array is an integer plus 0.5.

6 . The gas turbine engine according to claim 1 , wherein the first and second numbers of airfoils are different than one another.

7 . The gas turbine engine according to claim 1 , wherein the second angular spacing based upon a second effective number of total airfoils in the array that is different than the total number of airfoils.

8 . The gas turbine engine according to claim 7 , wherein the second effective number of total airfoils in the array is a fractional number.

9 . The gas turbine engine according to claim 8 , wherein the second angular spacing is 360° divided by the second effective number of total airfoils in the array.

10 . The gas turbine engine according to claim 9 , wherein the second effective number of total airfoils in the array is an integer plus 0.5.

11 . The gas turbine engine according to claim 8 , wherein the first effective number of total airfoils in the array is different than the second effective number of airfoils in the array.

12 . The gas turbine engine according to claim 11 , wherein the first effective number of airfoils in the array corresponds to the second effective number of airfoils in the array plus an integer.

13 . The gas turbine engine according to claim 1 , comprising a turbine section, wherein the array is arranged in the turbine section.

14 . The gas turbine engine according to claim 13 , wherein the turbine section includes a fixed stator section and a rotating section, the first and second number of airfoils arranged in the fixed stator section.

15 . The gas turbine engine according to claim 14 , wherein the array of airfoils is configured to produce a forcing function for the rotating section that is approximately 180° out of phase with a subsequent revolution of the rotating section.

16 . The gas turbine engine according to claim 1 , wherein the first and second effective numbers of total airfoils in the array are a fractional numbers.

17 . The gas turbine engine according to claim 16 , wherein the first and second angular spacings each respectively correspond to 360° divided by the first effective number of total airfoils in the array and 360° divided by the second effective number of total airfoils in the array.

18 . The gas turbine engine according to claim 17 , wherein the first effective number of total airfoils in the array is an integer plus 0.5, and the second effective number of total airfoils in the array is another integer plus 0.5.

Assignees

• United Technologies Corp

Inventors

• Simpson Alex J

Classifications

• F01D5/26

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F04D29/544

  Blade shapes · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title