Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-10605259-B2
Application number	US-201515115714-A
Country	US
Kind code	B2
Filing date	Feb 12, 2015
Priority date	Feb 19, 2014
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

An airfoil of a turbine engine 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 leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.

First claim

What is claimed is:

1. 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, wherein the fan section has a low fan pressure ratio of less than 1.55;
a geared architecture coupling the fan section to the turbine section or the compressor section; and
an airfoil 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 leading edge angle and span position that defines a curve with the leading edge angle of less than 40° at 100% span.

2. The gas turbine engine according to claim 1 , wherein the airfoil is arranged in the compressor section.

3. The gas turbine engine according to claim 2 , 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, the airfoil provided in a compressor outside the high pressure compressor section.

4. The gas turbine engine according to claim 3 , wherein the low pressure compressor is counter-rotating relative to the fan blades.

5. The gas turbine engine according to claim 3 , wherein the gas turbine engine is a two-spool configuration.

6. The gas turbine engine according to claim 3 , wherein the low pressure compressor is immediately downstream from the fan section.

7. The gas turbine engine according to claim 2 , wherein the airfoil is fixed relative to an engine axis of an engine static structure.

8. The gas turbine engine according to claim 1 , wherein the leading edge angle is less than 40° at 90% span.

9. The gas turbine engine according to claim 8 , wherein the leading edge angle is less than 40° at 80% span.

10. The gas turbine engine according to claim 9 , wherein the leading edge angle is less than 40° at 70% span.

11. The gas turbine engine according to claim 1 , wherein the curve has a negative slope from 90% span to 100% span and the leading edge angle is less than 40° from 90% span to 100% span.

12. The gas turbine engine according to claim 11 , wherein the leading edge angle has the negative slope from 80% span to 100% span and is less than 40° from 80% span to 100% span.

13. The gas turbine engine according to claim 1 , wherein the leading edge angle at 100% span is smaller than the leading edge angle at 50% span.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F04D29/544

  Blade shapes · CPC title

• F05D2240/121

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

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title