Compressor stator with leading edge fillet

Patent metadata

Field	Value
Publication number	US-11118466-B2
Application number	US-201816165501-A
Country	US
Kind code	B2
Filing date	Oct 19, 2018
Priority date	Oct 19, 2018
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

A compressor of a gas turbine engine includes a rotor and a stator located downstream of the rotor. The stator has a plurality of vanes each with an airfoil extending span-wise between a root proximate an inner hub of the stator and a tip. A fillet is disposed at the leading edge of the root of the airfoil, and extends between a pressure side surface of the airfoil and the inner hub.

First claim

The invention claimed is:

1. A compressor for a gas turbine engine, the compressor comprising: a rotor and a stator located downstream of the rotor, the stator comprising a plurality of vanes, each of the vanes having an airfoil extending generally radially from a root proximate an inner hub of the stator to a radially outer tip, a span of the airfoil defined between the root and the tip, the airfoil having a leading edge, a trailing edge, and a chord extending between the leading edge and the trailing edge to define a chord length, the airfoil having a pressure side surface and a suction side surface each extending on opposite sides of the airfoil between the leading edge and the trailing edge, and a fillet disposed at the root of the airfoil, the fillet extending upstream from the leading edge of a remainder of the airfoil, the fillet extending away from the pressure side surface a greater distance than the fillet extends away from the suction side surface, a height of the fillet taken in a spanwise direction is maximum at the leading edge, the fillet having a width in a direction normal to the pressure side of the remainder of the airfoil, the height and the width of the fillet decreasing from the leading edge such that the fillet blends smoothly into the pressure side of the reminder of the airfoil in a downstream direction, the fillet being disposed only on the pressure side surface of the airfoil, the suction side surface being free of the fillet.

2. The compressor as defined in claim 1 , wherein the fillet extends downstream from the leading edge.

3. The compressor as defined in claim 2 , wherein the fillet extends downstream from the leading edge a chord-wise distance of less than 50% of the chord length.

4. The compressor as defined in claim 3 , wherein the chord-wise distance is from 10% to 50% of the chord length.

5. The compressor as defined in claim 1 , wherein the fillet extends upstream from the leading edge a chord-wise distance of less than 20% of the chord length.

6. The compressor as defined in claim 5 , wherein the chord-wise distance is from 5% to 20% of the chord length.

7. The compressor as defined in claim 1 , wherein the fillet extends radially from the root along the leading edge.

8. The compressor as defined in claim 7 , wherein the fillet extends radially away from the root a span-wise distance of less than 10% of the span of the airfoil.

9. The compressor as defined in claim 8 , wherein the span-wise distance is from 2% to 10% of the span of the airfoil.

10. The compressor as defined in claim 1 , wherein the fillet has a fillet radius that is from 5% to 15% of the span of the airfoil.

11. The compressor as defined in claim 1 , wherein the fillet blends smoothly with the pressure side surface and the leading edge of the airfoil, and the inner hub of the stator.

12. The compressor as defined in claim 1 , wherein a first staggered angle is defined at the fillet, and a second staggered angle is defined at the leading edge of the airfoil at a point thereon outside of the fillet, the first staggered angle being greater than the second staggered angle, and wherein the first staggered angle is from 5 to 10 degrees greater than the second staggered angle.

13. A turbofan engine comprising a fan and a casing defining a bypass duct surrounding an engine core defining an annular gas passage, a fan stator disposed within the engine core downstream of the fan, the fan stator including a plurality of vanes circumferentially spaced-apart around a circumference of the fan stator within the annular gas passage, each of the vanes having an airfoil extending between a root and a tip spaced apart by a span of the airfoil, the airfoil having a leading edge and a trailing edge spaced apart along a chord line by a chord length of the airfoil, a pressure side surface and a suction side surface respectively extending on opposite sides of the airfoil between the leading edge and the trailing edge, and a leading edge fillet disposed at the root of the airfoil on the pressure side surface, the leading edge fillet having a height taken in a spanwise direction and a width in a direction normal to the pressure side, the height and the width decreasing from the leading edge such that the fillet blends smoothly into the pressure side of the reminder of the airfoil in a downstream direction, a first staggered angle defined at the fillet and a second staggered angle is defined at the leading edge of the airfoil at a point thereon radially above the fillet, the first staggered angle being from 5 to 10 degrees greater than the second staggered angle.

14. The turbofan engine of claim 13 , wherein the fillet extends upstream from the leading edge by a distance of 5-20% of the chord length.

15. The turbofan engine of claim 13 , wherein the fillet extends downstream from the leading edge by a distance of 10-50% of the chord length.

16. The turbofan engine of claim 13 , wherein the fillet extends radially away from the root by a distance of 2-10% of the span.

17. A compressor for a gas turbine engine, the compressor comprising: a rotor and a stator located downstream of the rotor, the stator comprising a plurality of vanes, each of the vanes having an airfoil extending generally radially from a root proximate an inner hub of the stator to a radially outer tip, a span of the airfoil defined between the root and the tip, the airfoil having a leading edge, a trailing edge, and a chord extending between the leading edge and the trailing edge to define a chord length, the airfoil having a pressure side surface and a suction side surface each extending on opposite sides of the airfoil between the leading edge and the trailing edge, and a fillet disposed at the root of the airfoil, the fillet extending upstream from the leading edge of a remainder of the airfoil, the fillet extending away from the pressure side surface a greater distance than the fillet extends away from the suction side surface, a height of the fillet taken in a spanwise direction is maximum at the leading edge, the fillet having a width in a direction normal to the pressure side of the remainder of the airfoil, the height and the width of the fillet decreasing from the leading edge such that the fillet blends smoothly into the pressure side of the reminder of the airfoil in a downstream direction, wherein a first staggered angle is defined at the fillet, and a second staggered angle is defined at the leading edge of the airfoil at a point thereon outside of the fillet, the first staggered angle being greater than the second staggered angle, and wherein the first staggered angle is from 5 to 10 degrees greater than the second staggered angle.

Assignees

• Pratt & Whitney Canada
• Pratt & Whiiney Canada Corp

Inventors

• Duong Hien
• Kandasamy Vijay

Classifications

• F01D5/145

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

• F05D2240/123

  related to the pressure side of a stator vane · CPC title

• F05D2260/00

  Function · CPC title

• F05D2240/121

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

• F04D29/544

  Blade shapes · CPC title