# US 11,306,594 B1 · Airfoil profile

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- Number: US 11,306,594 B1
- Document ID: US11306594B1
- Status: Granted
- Kind: B1
- Application number: 17/185,650
- Filed: 2021-02-25
- Granted: 2022-04-19
- Earliest claimed: 2021-02-25
- Assignees: Doosan Heavy Industries Construction Co., Ltd
- Applicants: Doosan Heavy Industries & Construction Co., Ltd.
- Inventors: Matthew D. Montgomery; William Brian Diggs; Jaewook Song; Jerry W. Wood; John Orosa
- Web page: https://patentgrep.com/patent/US11306594B1

## CPC

- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F04D 19/02: Multi-stage pumps
- F04D 29/324: {Blades}
- F04D 29/544: {Blade shapes}
- F01D 5/3007: {of axial insertion type}
- F05D 2220/3216: for a special compressor stage
- F05D 2240/301: Cross-sectional characteristics
- F05D 2250/74: given by a set or table of xyz-coordinates
- 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

## Abstract

Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

## Claims

### Claim 1

A compressor component comprising:
a root portion; and
an airfoil portion extending from the root portion, the airfoil portion having an uncoated nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system,
wherein at each Z distance, corresponding X and Y coordinates are connected by a smooth continuous arc to define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections are joined together by smooth continuous arcs to form the airfoil profile.

### Claim 2 (depends on 1)

The compressor component of claim 1, wherein the root portion and the airfoil portion form at least part of a compressor blade.

### Claim 3 (depends on 1)

The compressor component of claim 1, wherein the root portion is configured to couple with a first stage rotor disc of a compressor.

### Claim 4 (depends on 1)

The compressor component of claim 1, wherein the airfoil profile lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.

### Claim 5 (depends on 1)

The compressor component of claim 1, wherein the airfoil profile lies within an envelope of +/−0.080 inches measured in a direction normal to any of the plurality of airfoil profile sections.

### Claim 6 (depends on 1)

The compressor component of claim 1, wherein the airfoil profile lies within an envelope of +/−0.020 inches measured in a direction normal to any of the plurality of airfoil profile sections.

### Claim 7 (depends on 1)

The compressor component of claim 1, further comprising a coating applied to the airfoil profile, the coating having a thickness of less than or equal to 0.010 inches.

### Claim 8

A compressor blade, comprising:
an airfoil portion having an uncoated nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinate values are distances in inches measured in a Cartesian coordinate system,
wherein at each Z distance, corresponding X and Y coordinates are connected by a smooth continuous arc to define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections are joined together by smooth continuous arcs to define the airfoil profile.

### Claim 9 (depends on 8)

The compressor blade of claim 8, wherein the X and Y coordinate values are scalable as a function of a same constant or number and a set of corresponding nominal Z coordinate values are scalable as a function of the same constant or number to provide at least one of a scaled up or a scaled down airfoil.

### Claim 10 (depends on 9)

The compressor blade of claim 9, wherein the compressor blade is configured to couple with rotor discs having different sized radiuses, wherein the Z coordinate values set forth in Table 1 are offset by a distance equal to a difference in rotor disc radius to provide at least one of a radially outward offset or radially inward offset airfoil shape.

### Claim 11 (depends on 8)

The compressor blade of claim 8, wherein the airfoil profile lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.

### Claim 12 (depends on 8)

The compressor blade of claim 8, wherein the airfoil profile provides the compressor blade with a first bending natural frequency between 130 Hz and 160 Hz when scaled for use in a compressor with a 60 Hz rotation speed.

### Claim 13 (depends on 8)

The compressor blade of claim 8, wherein the airfoil profile provides the compressor blade with a second bending natural frequency that differs by at least 5% from 5th, 6th, and 7th engine order excitations.

### Claim 14 (depends on 8)

The compressor blade of claim 8, further comprising a coating applied to the airfoil profile, the coating having a thickness of less than or equal to 0.010 inches.

### Claim 15

A compressor, comprising:
a casing;
a rotor disc positioned within the casing; and
a plurality of compressor blades coupled to the rotor disc, the plurality of compressor blades circumferentially spaced around the rotor disc about a center axis of the compressor, wherein each compressor blade of the plurality of compressor blades has an airfoil comprising:
an airfoil portion having an uncoated nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinate values are distances in inches measured in a Cartesian coordinate system,
wherein at each Z distance, corresponding X and Y coordinates are connected by a smooth continuous arc to define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections are joined together by smooth continuous arcs to define the airfoil profile.

### Claim 16 (depends on 15)

The compressor of claim 15, wherein the rotor disc and the plurality of compressor blades form a compressor stage zero.

### Claim 17 (depends on 15)

The compressor of claim 15, wherein the airfoil profile lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.