# US 8,464,426 B2 · Gas turbine engine airfoil

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- Number: US 8,464,426 B2
- Document ID: US8464426B2
- Status: Granted
- Kind: B2
- Application number: 13/437,040
- Filed: 2012-04-02
- Published: 2012-08-02
- Granted: 2013-06-18
- Earliest claimed: 2008-12-17
- Assignees: United Technologies Corporation
- Applicants: Jody Kirchner; Yuan Dong; Sanjay S. Hingorani
- Inventors: Jody Kirchner; Yuan Dong; Sanjay S. Hingorani
- Web page: https://patentgrep.com/patent/US8464426B2

## CPC

- F01D 5/12: Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02)
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F04D 29/324: {Blades}
- F05D 2240/301: Cross-sectional characteristics
- Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
- Y10T 29/49336: Blade making
- Y10T 29/49337: Composite blade
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.

## Claims

### Claim 1

A method of designing an airfoil for a gas turbine engine, comprising the steps of:
a) localizing a sweep angle at a leading edge of a tip region of the airfoil; and
b) localizing a dihedral angle at the tip region of the airfoil, wherein the dihedral angle is applied by translating the airfoil in direction normal to a chord of the airfoil.

### Claim 2 (depends on 1)

The method as recited in claim 1, wherein the sweep angle is a forward sweep angle.

### Claim 3 (depends on 1)

The method as recited in claim 1, wherein said step a) includes the step of:
displacing a plurality of airfoil sections of the airfoil parallel to the chord relative to a base-line rotor blade design.

### Claim 4 (depends on 1)

The method as recited in claim 1, wherein the dihedral angle is a positive dihedral angle.

### Claim 5 (depends on 1)

The method as recited in claim 1, wherein said step b) includes the step of:
displacing a plurality of airfoil sections of the airfoil tangentially to the chord relative to a base-line rotor blade design.

### Claim 6 (depends on 1)

The method as recited in claim 1, comprising the step of:
c) extending the sweep angle and the dihedral angle over a distance of the airfoil equivalent to about 10% to about 40% of a span of the airfoil.

### Claim 7 (depends on 6)

The method as recited in claim 6, wherein said step c) includes the step of:
extending the sweep angle and the dihedral angle from an outer edge of the tip region radially inward along a radial axis over a distance equal to about 10% to about 40% of the span.