Subsonic swept fan blade

Patent metadata

Field	Value
Publication number	US-9790797-B2
Application number	US-201113176540-A
Country	US
Kind code	B2
Filing date	Jul 5, 2011
Priority date	Jul 5, 2011
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be driven at a at a design speed by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool. Rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades includes an airfoil body. The leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a spool;
a turbine coupled with said spool;
a propulsor coupled to be rotated at a design speed about an axis by said turbine through said spool; and
a gear assembly coupled between said propulsor and said spool such that rotation of said turbine drives said propulsor at a different speed than said spool,
wherein said propulsor includes a hub and a row of propulsor blades that extend from said hub, each of said propulsor blades includes an airfoil body that extends in a radial span between a root and a tip, in a chord direction between a leading edge and a trailing edge and in a thickness direction between a pressure side and a suction side, said leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span,
wherein said swept profile has a rearward sweep from 0% to at least 50% of the radial span and a forward sweep from at least 60% to 100% of said radial span, with said root being at 0% of said radial span and said tip being at 100% of said radial span, said rearward sweep has a sweep angle of less than 15°, and said swept profile has a single, exclusive transition between a rearward sweep and a forward sweep from 0% to 100% of said radial span.

2. The gas turbine engine as recited in claim 1 , wherein said rearward sweep has a sweep angle that decreases from 0% to at least 50% of said radial span.

3. The gas turbine engine as recited in claim 1 , wherein said rearward sweep has a sweep angle between 5° and 10° from 0% to 50% of said radial span.

4. The gas turbine engine as recited in claim 1 , wherein said transition is between 50% and 60% of said radial span.

5. The gas turbine engine as recited in claim 1 , wherein said transition is between 55% and 60% of said radial span.

6. The gas turbine engine as recited in claim 1 , wherein a percentage S REAR of said radial span is said rearward sweep and a percentage S FOR of the radial span is said forward sweep, and a ratio of S REAR /S FOR is between 0.67 and 1.5.

7. The gas turbine engine as recited in claim 6 , wherein said ratio is between 1.25 and 1.30.

8. The gas turbine engine as recited in claim 1 , wherein said design speed is at full throttle.

9. The gas turbine engine as recited in claim 1 , wherein said propulsor includes a number (N) of said propulsor blades in the row that is no more than 20, said propulsor blades have a solidity value with regard to a chord dimension (CD) at the tips and a circumferential pitch (CP), and said solidity value is a ratio (R) of CD/CP that is between 0.6 and 1.3.

10. The gas turbine engine as recited in claim 9 , wherein a ratio N/R is between 8 and 28.

Assignees

• Gallagher Edward J
• Rogers Thomas H
• United Technologies Corp

Inventors

• Gallagher Edward J
• Rogers Thomas H

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D5/141 Primary

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

• F05D2240/303

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

• F05D2240/302

  characteristics related to shock waves, transonic or supersonic flow · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic