# US 10,309,414 B2 · Gas turbine engine airfoil

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- Number: US 10,309,414 B2
- Document ID: US10309414B2
- Status: Granted
- Kind: B2
- Application number: 15/470,462
- Filed: 2017-03-27
- Published: 2017-07-06
- Granted: 2019-06-04
- Earliest claimed: 2014-02-19
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Edward J. Gallagher; Byron R. Monzon; Ling Liu; Linda S. Li; Darryl Whitlow; Barry M. Ford
- Web page: https://patentgrep.com/patent/US10309414B2

## CPC

- F04D 29/325: {for axial flow fans (blade mountings F04D29/34, blades F04D29/38)}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F02K 3/06: with front fan
- F04D 19/002: {Axial flow fans}
- F04D 29/324: {Blades}
- F04D 29/384: {characterised by form}
- F05D 2220/32: in gas turbines
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.

## Claims

### Claim 1

An airfoil for a turbine engine comprising:
an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning,
wherein the airfoil has a leading edge sweep angle curve corresponding to a relationship between a leading edge sweep angle and a span position, wherein a leading edge sweep angle at the 100% span position is less negative than a forward-most leading edge sweep angle along the curve, and wherein the curve has a decreasing leading edge sweep angle rate in a range of a 80-100% span position, and wherein the airfoil is a fan blade for the turbine engine.

### Claim 2 (depends on 1)

The airfoil according to claim 1, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 50-70% span position.

### Claim 3 (depends on 2)

The airfoil according to claim 2, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 60-70% span position.

### Claim 4 (depends on 1)

The airfoil according to claim 1, wherein the trailing edge sweep angle transitions from less positive to more positive at greater than an 80% span position.

### Claim 5 (depends on 1)

The airfoil according to claim 1, wherein a positive-most trailing edge sweep angle is at a greater than 50% span position.

### Claim 6 (depends on 1)

The airfoil according to claim 1, wherein a positive-most trailing edge sweep angle is at about a 70% span position.

### Claim 7 (depends on 1)

The airfoil according to claim 1, wherein the trailing edge sweep angle is within 5° along a portion of the curve from the 0% span position to a 60% span position.

### Claim 8 (depends on 7)

The airfoil according to claim 7, wherein a positive-most trailing edge sweep angle lies along the portion.

### Claim 9 (depends on 1)

The airfoil according to claim 1, wherein the leading edge sweep angle curve has a portion extending span-wise toward the tip and from the forward-most leading edge sweep angle, the portion has a decreasing leading edge sweep angle that crosses a zero sweep angle in the range of a 30-40% span position.

### Claim 10 (depends on 9)

The airfoil according to claim 9, wherein the forward-most leading edge sweep angle is in a range of −10° to −15°.

### Claim 11 (depends on 10)

The airfoil according to claim 10, wherein the forward-most leading edge sweep angle is about −10°.

### Claim 12 (depends on 10)

The airfoil according to claim 10, wherein a rearward-most leading edge sweep angle is in a range of 15° to 30°.

### Claim 13 (depends on 10)

The airfoil according to claim 10, wherein the leading edge sweep angle at the 0% span position and a leading edge sweep angle at the 100% span position are within 5° of one another.

### Claim 14 (depends on 10)

The airfoil according to claim 10, wherein the leading edge sweep angle at the 0% span position is negative, and a leading edge sweep angle at the 100% span position is positive.

### Claim 15 (depends on 10)

The airfoil according to claim 10, wherein the leading edge sweep angle at the 0% span position is positive, and a leading edge sweep angle at the 100% span position is negative.

### Claim 16 (depends on 1)

The airfoil according to claim 1, wherein the leading edge dihedral at the 0% span position is in the range of −3° to −12°.

### Claim 17 (depends on 16)

The airfoil according to claim 16, wherein the leading edge dihedral at the 0% span position is about −4°.

### Claim 18 (depends on 2)

The airfoil according to claim 2, wherein the leading edge dihedral at the 0% span position is about −10°.

### Claim 19 (depends on 16)

The airfoil according to claim 16, wherein the leading edge dihedral extends from the 0% span position to a 20% span position having a leading edge dihedral in a range of −2° to −6°.

### Claim 20 (depends on 19)

The airfoil according to claim 19, wherein the leading edge dihedral includes a first point at a 75% span position and extends generally linearly from the first point to a second point at the 85% span position.

### Claim 21 (depends on 16)

The airfoil according to claim 16, wherein a maximum negative leading edge dihedral is in a range of 95-100% span position.

### Claim 22 (depends on 21)

The airfoil according to claim 21, wherein a least negative leading edge dihedral is in a range of 5-15% span position.

### Claim 23 (depends on 16)

The airfoil according to claim 16, wherein a maximum negative leading edge dihedral is in a range of 65-75% span position.

### Claim 24 (depends on 23)

The airfoil according to claim 23, wherein a least negative leading edge dihedral is in a range of 0-10% span position.

### Claim 25 (depends on 16)

The airfoil according to claim 16, wherein a maximum negative leading edge dihedral is in a range of 50-60% span position.

### Claim 26 (depends on 1)

The airfoil according to claim 1, wherein the airfoil has a relationship between a trailing edge dihedral and a span position, the trailing edge dihedral positive from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.