Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-10890195-B2
Application number	US-201916667321-A
Country	US
Kind code	B2
Filing date	Oct 29, 2019
Priority date	Feb 19, 2014
Publication date	Jan 12, 2021
Grant date	Jan 12, 2021

Abstract

A compressor airfoil of a turbine engine that has a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.

First claim

What is claimed is:

1. A compressor airfoil of a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a non-linear curve with a non-negative slope from 0% span to 60% span corresponding to a non-decreasing trailing edge angle.

2. The compressor airfoil according to claim 1 , wherein the curve has a non-negative slope from 0% span to 80% span.

3. The compressor airfoil according to claim 2 , wherein the curve has a non-negative slope from 0% span to 100% span.

4. A compressor airfoil of a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a curve with a positive slope from 0% span to 100% span.

5. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades; and
an airfoil arranged in the compressor section and including pressure and suction sides and extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a non-linear curve with a non-negative slope from 0% span to 60% span corresponding to a non-decreasing trailing edge angle.

6. The gas turbine engine according to claim 5 , wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section.

7. The gas turbine engine according to claim 6 , wherein the airfoil is provided in a compressor outside the high pressure compressor.

8. The gas turbine engine according to claim 7 , wherein the low pressure compressor is counter-rotating relative to the fan blades.

9. The gas turbine engine according to claim 7 , wherein the gas turbine engine is a two-spool configuration.

10. The gas turbine engine according to claim 7 , wherein the low pressure compressor is immediately downstream from the fan section.

11. The gas turbine engine according to claim 6 , wherein the airfoil is fixed relative to an engine static structure.

12. The gas turbine engine according to claim 5 , wherein the curve has a non-negative slope from 0% span to 80% span.

13. The gas turbine engine according to claim 12 , wherein the curve has a non-negative slope from 0% span to 100% span.

14. The gas turbine engine according to claim 5 , wherein the fan section has a low fan pressure ratio of less than 1.55.

15. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades; and
an airfoil arranged in the compressor section and including pressure and suction sides and extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a curve with a positive slope from 0% span to 100% span.

16. The gas turbine engine according to claim 15 , wherein the fan section has a low fan pressure ratio of less than 1.55.

Assignees

• Raytheon Tech Corp

Inventors

• Gallagher Edward J
• Brilliant Lisa I
• Straccia Joseph C
• Balamucki Stanley J
• Stephens Mark A
• Hudon Kate

Classifications

• F01D5/141 Primary

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

• F04D29/324

  Blades · CPC title

• F05D2240/122

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

• F02K3/072

  with counter-rotating {, e.g. fan} rotors · CPC title

• F05D2220/3217

  for the first stage of a compressor or a low pressure compressor · CPC title