Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-10570915-B2
Application number	US-201515113916-A
Country	US
Kind code	B2
Filing date	Feb 16, 2015
Priority date	Feb 19, 2014
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 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, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor 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, wherein the low pressure compressor is downstream from the fan section, and wherein the low pressure compressor is counter-rotating relative to the fan blades;
a geared architecture coupling the fan section to the turbine section or the compressor section;
an airfoil arranged in the low pressure compressor and including 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 camber angle and a span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span, and
wherein the camber angle is less than 20° within the entire range of 40% span to 100% span.

2. The gas turbine engine according to claim 1 , wherein the gas turbine engine is a two-spool configuration.

3. The gas turbine engine according to claim 1 , wherein the airfoil is rotatable relative to an engine static structure.

4. The gas turbine engine according to claim 1 , wherein the curve has a decreasing camber angle within the range of 60% span to 100% span.

5. The gas turbine engine according to claim 1 , wherein the camber angle is generally linear within the range of 0% span to 100% span.

6. The gas turbine engine according to claim 5 , wherein the camber angle is less than 20° within the range of 80% span to 100% span.

7. The gas turbine engine according to claim 6 , wherein the camber angle is less than 20° within the range of 60% span to 100% span.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F05D2220/3217

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

• F02K3/072

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

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F01D5/141

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