Turbomachine airfoil positioning

Patent metadata

Field	Value
Publication number	US-9435221-B2
Application number	US-201313963689-A
Country	US
Kind code	B2
Filing date	Aug 9, 2013
Priority date	Aug 9, 2013
Publication date	Sep 6, 2016
Grant date	Sep 6, 2016

Abstract

Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.

First claim

What is claimed is:

1. A turbomachine comprising:
a diffuser;
a plurality of airfoil rows, including:
a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades;
a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and
a third airfoil row of the first type adjacent the second airfoil row,

wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.

2. The turbomachine of claim 1 , selected from a group consisting of: a turbine, an engine, and a compressor.

3. The turbomachine of claim 2 , wherein the turbomachine is a gas turbine.

4. The turbomachine of claim 1 , wherein the at least one of the plurality of airfoil rows is clocked to a first relative position that exhibits a first variation in airflow pressure at the at least one point on the surface of the diffuser that is less than a second variation in airflow pressure at the at least one point in the diffuser exhibited at a second relative position.

5. The turbomachine of claim 4 , wherein the first and second variations are calculated using the relative positions of the at least one airfoil row and another airfoil row of the turbomachine.

6. The turbomachine of claim 5 , wherein the first and second variations are calculated using computational fluid dynamics equations.

7. The turbomachine of claim 6 , wherein the computational fluid dynamics equations include Navier-Stokes equations.

8. The turbomachine of claim 1 , wherein the at least one of the plurality of airfoil rows clocked includes the third airfoil row.

9. The turbomachine of claim 8 , wherein the first and third airfoil rows are rows of rotating blades and the second airfoil row is a row of stationary vanes.

10. A method of reducing variation in airflow pressure entering a diffuser of a turbomachine, the method comprising:
while operating the turbomachine, calculating airflow across at least three airfoil rows of the turbomachine, the at least three airfoil rows including:
a first airfoil row adjacent a diffuser of the turbomachine, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades;
a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and
a third airfoil row of the first type adjacent the second airfoil row;
evaluating a pressure variation at at least one spanwise location of the diffuser; and
determining whether the pressure variation is within a predetermined target,

wherein, in the case that the pressure variation is not within the predetermined target, the method further includes:
changing a relative clocking position of at least one of the at least three airfoil rows;
recalculating airflow across the at least three airfoil rows;
reevaluating the pressure variation at the at least one spanwise location of the diffuser; and
determining whether the reevaluated pressure variation is within the predetermined target.

11. The method of claim 10 , wherein changing the relative clocking position includes changing the clocking position of an airfoil row other than the first, second, or third airfoil rows.

12. The method of claim 10 , wherein calculating the airflow includes the use of computational fluid dynamics equations.

13. The method of claim 12 , wherein the computational fluid dynamics equations include Navier-Stokes solver equations.

14. A method of reducing variation in airflow pressure entering a diffuser of a turbomachine, the method comprising:
while operating the turbomachine, calculating airflow across at least three airfoil rows of the turbomachine;
evaluating a first pressure variation at at least one spanwise location of a diffuser of the turbomachine;
changing a relative clocking position of at least one of the at least three airfoil rows;
recalculating airflow across the at least three airfoil rows;
evaluating a second pressure variation at the at least one spanwise location of the diffuser;
determining whether the second pressure variation is less than the first pressure variation; and
in the case that the second pressure variation is less than the first pressure variation, operating the turbomachine using the changed relative clocking position of the at least one airfoil row.

15. The method of claim 14 , wherein the at least three airfoil rows includes:
a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades;
a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and
a third airfoil row of the first type adjacent the second airfoil row.

16. The method of claim 15 , wherein changing the relative clocking position includes changing the clocking position of an airfoil row other than the first, second, or third airfoil rows.

17. The method of claim 14 , wherein calculating the airflow includes using computational fluid dynamics equations.

18. The method of claim 17 , wherein the computational fluid dynamics equations include Navier-Stokes solver equations.

Assignees

• Gen Electric

Inventors

• Smith Paul Kendall

Classifications

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D5/142

  of the blades of successive rotor or stator blade-rows · CPC title