Turbomachine having a gas flow aeromechanic system and method

Patent metadata

Field	Value
Publication number	US-2016201571-A1
Application number	US-201615075453-A
Country	US
Kind code	A1
Filing date	Mar 21, 2016
Priority date	Oct 3, 2011
Publication date	Jul 14, 2016
Grant date	—

Abstract

A turbomachine including an improved backflow margin includes a combustor portion fluidly connected to a turbine portion. The turbine portion includes a gas path, a first stage having a first plurality of airfoil members arranged along the gas path, and a second stage having a second plurality of airfoil members arranged along the gas path downstream from the first stage. The first plurality of airfoil members are configured to intercept combustion gases from the combustor portion at a first momentum and create a wake zone having a second momentum that is lower than the first momentum. The turbomachine includes a gas flow aeromechanics system configured and disposed to improve gas flow aeromechanics along the gas path by circumferentially clocking the second plurality of airfoil members relative to the first plurality of airfoil members to intercept the wake zone at the second momentum.

First claim

1 . A method for improving gas flow aeromechanics in a turbomachine, the method comprising:
guiding combustion gases having a first momentum toward a first plurality of airfoil members arranged along a gas path of a turbine; passing the combustion gases at the first momentum over the first plurality of airfoil members; forming a wake zone downstream from the first plurality of airfoil members, the wake zone having a second momentum that is lower than the first momentum; positioning a leading edge of a second plurality of airfoil members downstream from the first plurality of airfoil members so as to intercept the wake zone; and reducing aeromechanic forces between the first plurality of airfoil members and the second plurality of airfoil members to improve aeromechanics along the gas path.

2 . The method according to claim 1 , wherein guiding the combustion gases toward the first plurality of airfoil members includes guiding the combustion gases toward a plurality of stationary airfoil members.

3 . The method according to claim 1 , wherein positioning the leading edge of the second plurality of airfoil members includes positioning the leading edge of a plurality of stationary airfoil members to intercept the wake zone.

4 . The method according to claim 1 , wherein positioning the leading edge of the second plurality of airfoil members to intercept the wake zone includes clocking the second plurality of airfoil members relative to the first plurality of airfoil members.

5 . The method of claim 1 , wherein improving gas flow aeromechanics within the gas path includes improving aeromechanics on a third plurality of airfoil members arranged between the first plurality of airfoil members and the second plurality of airfoil members.

6 . The method of claim 1 , wherein improving gas flow aeromechanics within the gas path includes reducing a bow wave upstream of the second plurality of airfoil members.

7 . The method of claim 1 , wherein improving gas flow aeromechanics within the gas path includes improving gas flow margin between the first plurality of airfoil members and the second plurality of airfoil members and reducing a bow wave upstream of the second plurality of airfoil members.

8 . A method for improving gas flow aeromechanics in a turbomachine, the method comprising:
guiding combustion gases having a first momentum toward a first plurality of stationary airfoil members arranged along a gas path of a turbine; passing the combustion gases at the first momentum over the first plurality of stationary airfoil members; forming a wake zone downstream from the first plurality of stationary airfoil members, the wake zone having a second momentum that is lower than the first momentum; and positioning a leading edge of a second plurality of stationary airfoil members downstream from the first plurality of stationary airfoil members so as to intercept the wake zone thereby reducing a bow wave between the first plurality of stationary airfoil members and the second plurality of stationary airfoil members.

9 . The method according to claim 8 , wherein positioning the leading edge of the second plurality of stationary airfoil members includes positioning the leading edge of a plurality of stationary airfoil members to intercept the wake zone.

10 . The method according to claim 8 , wherein positioning the leading edge of the second plurality of stationary airfoil members to intercept the wake zone includes clocking the second plurality of stationary airfoil members relative to the first plurality of stationary airfoil members.

11 . The method of claim 8 , wherein improving gas flow aeromechanics within the gas path includes improving aeromechanics on a third plurality of stationary airfoil members arranged between the first plurality of stationary airfoil members and the second plurality of stationary airfoil members.

12 . The method of claim 8 , wherein improving gas flow aeromechanics within the gas path includes reducing a bow wave upstream of the second plurality of stationary airfoil members.

Assignees

• Gen Electric

Inventors

• Stein Alexander

Classifications

• F02C9/16 Primary

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• F05D2260/71

  as a function of flow velocity · CPC title

• F05D2260/70

  Adjusting of angle of incidence or attack of rotating blades · CPC title

• F01D9/041

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

• F05D2240/35

  Combustors or associated equipment · CPC title