Gas turbine engine airfoil curvature

Patent metadata

Field	Value
Publication number	US-9938854-B2
Application number	US-201514712067-A
Country	US
Kind code	B2
Filing date	May 14, 2015
Priority date	May 22, 2014
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a rotating stage including an array of blades having a vibratory mode; and
a fixed stage of stator vanes having an array of airfoils arranged immediately upstream from the array of blades, each airfoil including a first circumferentially extreme position at a first same span position, the first circumferentially extreme positions of each airfoil circumferentially spaced apart from one another a pitch, each airfoil including a second circumferentially extreme position at a second same span position that is different than the first same span location, the second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position of a same airfoil in the array of airfoils by a pitch spacing that is in a range of 0.5-1.0 times the pitch, wherein the array of airfoils is configured to produce a radial alternating pressure amplitude and phase distribution on the array of blades that does not excite the vibratory mode thereby avoiding damage to the array of blades.

2. The gas turbine engine according to claim 1 , wherein the first same span position is one radial end of each airfoil.

3. The gas turbine engine according to claim 2 , wherein the second same span position is another radial end of each airfoil opposite the one radial end.

4. The gas turbine engine according to claim 2 , wherein each airfoil includes another radial end opposite the one radial end, the second same span position located radially between the one radial end and the other radial end.

5. The gas turbine engine according to claim 1 , wherein the pitch spacing is the pitch.

6. The gas turbine engine according to claim 1 , wherein the stator vanes include inner and outer platforms, each airfoil extending radially between and joining the inner and outer platforms.

7. The gas turbine engine according to claim 6 , wherein the first and second same span positions are provided by each airfoil at the inner and outer platforms.

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

Assignees

• United Technologies Corp

Inventors

• Simpson Alex J
• Nash Timothy Charles

Classifications

• F01D5/141

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

• 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

• F01D5/22

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D9/04

  forming ring or sector · CPC title