Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-10570916-B2
Application number	US-201515115360-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 an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.

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 fan pressure ratio of less than 1.55, wherein the low pressure compressor is counter-rotating relative to the fan blades, wherein the low pressure compressor is downstream from the fan section;
a geared architecture coupling the fan section to the turbine section or the compressor section; and
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 an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span, where the negative slope leans forward relative to an engine axis.

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 negative slope is from 80% span to 100% span.

5. The gas turbine engine according to claim 4 , wherein the negative slope is from 70% span to 100% span.

6. The gas turbine engine according to claim 1 , wherein the curve has a positive slope beginning at 0% span, where the positive slope leans aftward relative to the engine axis.

7. The gas turbine engine according to claim 6 , wherein the positive slope extends from 0% span to 40% span.

8. The gas turbine engine according to claim 7 , wherein the curve transitions from the positive slope to the negative slope in a range of 40% span to 75% span.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F04D29/324 Primary

  Blades · CPC title

• F01D5/14

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F01D5/141

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

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F04D29/544

  Blade shapes · CPC title