Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-2022106965-A1
Application number	US-202117551349-A
Country	US
Kind code	A1
Filing date	Dec 15, 2021
Priority date	Feb 19, 2014
Publication date	Apr 7, 2022
Grant date	—

Abstract

An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.

First claim

What is claimed is:

1 . An airfoil for a gas turbine engine comprising:
a pressure side and a suction side extending in a radially outward direction from a 0% span position to a 100% span position; wherein the airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis; wherein the airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span; and wherein the stagger angle at 100% span is greater than the stagger angle at 50% span.

2 . The airfoil according to claim 1 , wherein the airfoil is a low pressure compressor blade.

3 . The airfoil according to claim 1 , wherein the stagger angle is between 55° and 65° at 100% span.

4 . The airfoil according to claim 1 , wherein the stagger angle is between 35° and 45° at 0% span.

5 . The airfoil according to claim 4 , wherein the stagger angle is between 55° and 65° at 100% span.

6 . The airfoil according to claim 1 , wherein the stagger angle has a positive slope from 20% span to 100% span.

7 . The airfoil according to claim 1 , wherein the curve includes a non-increasing positive slope in a range of 80% span to 100% span.

8 . The airfoil according to claim 1 , wherein the curve includes a negative slope in a range of 80% span to 100% span.

9 . A gas turbine engine comprising:
a fan section including a fan; a compressor section including a low pressure compressor and a high pressure compressor; a turbine section including a low pressure turbine and a high pressure turbine, the low pressure turbine coupled to the fan; wherein the compressor section includes an airfoil, the airfoil including a pressure side and a suction side extending in a radially outward direction from a 0% span position to a 100% span position; wherein the airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis; wherein the airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span; and wherein the stagger angle at 100% span is greater than the stagger angle at 50% span.

10 . The gas turbine engine according to claim 9 , wherein the stagger angle is between 55° and 65° at 100% span.

11 . The gas turbine engine according to claim 9 , wherein the stagger angle is between 35° and 45° at 0% span.

12 . The gas turbine engine according to claim 11 , wherein the stagger angle is between 55° and 65° at 100% span.

13 . The gas turbine engine according to claim 12 , wherein the curve includes a non-increasing positive slope in a range of 80% span to 100% span.

14 . The gas turbine engine according to claim 12 , wherein the curve includes a negative slope in a range of 80% span to 100% span.

15 . The gas turbine engine according to claim 12 , wherein the high pressure compressor excludes the airfoil.

16 . The gas turbine engine according to claim 15 , wherein the fan section has an array of twenty-six or fewer fan blades.

17 . The gas turbine engine according to claim 16 , wherein the fan section has a low pressure ratio of less than 1.55 at cruise at about 0.8 Mach and about 35,000 feet.

18 . The gas turbine engine according to claim 17 , wherein the airfoil is a rotatable blade.

19 . The gas turbine engine according to claim 18 , wherein the low pressure compressor counter-rotates relative to the fan blades in operation.

Assignees

• United Technologies 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

• 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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title