Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith

Patent metadata

Field	Value
Publication number	US-9784285-B2
Application number	US-201414485163-A
Country	US
Kind code	B2
Filing date	Sep 12, 2014
Priority date	Sep 12, 2014
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.

First claim

What is claimed is:

1. A variable stator vane comprising:
an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis, the inner and outer buttons each having a button forward edge portion and the airfoil including leading and trailing edges, pressure and suction sides, and a root and a tip; and
wherein:
the leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root and a local aft sweep at the tip, thereby forming a locally swept root and tip of the leading edge;
the button forward edge portion of the outer button is substantially vertically aligned with the locally swept leading edge tip thereat; and
the button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root thereat.

2. The variable stator vane of claim 1 , wherein the leading edge of the airfoil includes the local forward sweep at the root of the airfoil in a hub region of a compressor in a gas turbine engine.

3. The variable stator vane of claim 1 , wherein the leading edge of the airfoil includes the local aft sweep at the tip of the airfoil in a shroud region of a compressor.

4. The variable stator vane of claim 1 , wherein the button forward edge portion of both the inner and outer buttons substantially covers the leading edge of the airfoil at both the root and the tip.

5. The variable stator vane of claim 1 , wherein a sweep offset of the local forward sweep is −15° or less to minimize a leading edge endwall gap at the root.

6. The variable stator vane of claim 1 , wherein the local forward sweep at the root extends from 0 up to 25% of the blade span and the local aft sweep at the tip extends from about 75% up to 100% of the blade span to minimize leading edge endwall gaps at the root and the tip.

7. The variable stator vane of claim 1 , wherein a sweep offset of the local aft sweep is 15° or greater to minimize leading edge endwall gaps.

8. A variable stator vane assembly comprising:
an inner and an outer button spaced apart and centered about a rotational axis, each of the inner and outer buttons having an edge circumscribed about the rotational axis at a button radius, the edge comprising a button forward edge portion and a button aft edge portion;
at least one annular row of variable stator vanes, each variable stator vane in the at least one annular row comprising:
an airfoil disposed between the spaced apart inner and outer buttons, the airfoil including leading and trailing edges, pressure and suction sides, and a root and a tip; and
wherein the leading edge, at least a portion of which extends forward of the buttons, of the airfoil includes a local forward sweep at the root and a local aft sweep at the tip, thereby forming a locally swept root and tip of the leading edge, the button forward edge portion of the outer button is substantially vertically aligned with the locally swept leading edge tip thereat, and the button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root thereat.

9. The variable stator vane assembly of claim 8 , wherein, for each variable stator vane in the at least one annular row, the leading edge of the airfoil includes the local forward sweep at the root of the airfoil in a hub region of a compressor in a gas turbine engine.

10. The variable stator vane assembly of claim 8 , wherein, for each variable stator vane in the at least one annular row, the leading edge of the airfoil includes the local aft sweep at the tip of the airfoil in a shroud region of a compressor.

11. The variable stator vane assembly of claim 8 , wherein, for each variable stator vane in the at least one annular row, the button forward edge portions of the inner and outer buttons substantially cover the leading edge of the airfoil at the root and the tip.

12. The variable stator vane assembly of claim 8 , wherein, for each variable stator vane in the at least one annular row, the local forward sweep at the root extends from 0 up to 25% of the blade span and the local aft sweep at the tip extends from about 75% up to 100% of the blade span wherein a sweep offset of the local forward sweep is −15° or less and the sweep offset of the local aft sweep is 15° or greater to minimize leading edge endwall gaps at the root and the tip.

13. A method for minimizing endwall leakage in a variable stator vane assembly, the method comprising:
providing a variable stator vane for the variable stator vane assembly having spaced apart inner and outer buttons centered about a rotational axis, the variable stator vane comprising an airfoil including leading and trailing edges, pressure and suction sides, and a root and a tip, the leading edge, at least a portion of which extends forward of the buttons, including a local forward sweep at the root with a sweep offset of −15° or less and a local aft sweep at the tip with the sweep offset of 15° or greater, thereby forming a locally swept root and tip of the leading edge to minimize leading edge endwall gaps at the root and the tip; and
disposing the variable stator vane between the spaced apart inner and outer buttons, the inner and outer buttons each having a button forward edge portion, the variable stator vane being disposed such that the button forward edge portion of the outer button is substantially vertically aligned with the locally swept leading edge of the airfoil at the tip and the button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge at the root.

14. The method of claim 13 , wherein the step of providing a variable stator vane comprises providing the leading edge of the airfoil with the local forward sweep at the root of the airfoil in a hub region of a compressor in a gas turbine engine.

15. The method of claim 13 , wherein the step of providing a variable stator vane comprises providing the leading edge of the airfoil with the local aft sweep at the tip of the airfoil in a shroud region of a compressor.

Assignees

• Honeywell Int Inc

Inventors

• Reynolds Bruce David
• Gentry Timothy
• Conner Richard David

Classifications

• F04D29/544 Primary

  Blade shapes · CPC title

• F01D5/141

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

• F05D2250/70

  Shape · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title