# US 12,215,598 B1 · Compressor rotor blade airfoils

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- Number: US 12,215,598 B1
- Document ID: US12215598B1
- Status: Granted
- Kind: B1
- Application number: 18/497,452
- Filed: 2023-10-30
- Granted: 2025-02-04
- Earliest claimed: 2023-10-30
- Assignees: GE Infrastructure Technology LLC
- Applicants: GE Infrastructure Technology LLC
- Inventors: Matthew John McKeever; Grady Pastor; Andrew Joseph Kotnour; Juliano Avolio; Kevin Michael Barnett; Laia Ferrer-Argemi
- Web page: https://patentgrep.com/patent/US12215598B1

## CPC

- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F05D 2220/3219: for the last stage of a compressor or a high pressure compressor
- F05D 2240/306: related to the suction side of a rotor blade
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- 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

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

## Claims

### Claim 1

A rotor blade comprising:
an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

### Claim 2 (depends on 1)

The rotor blade of claim 1, wherein the airfoil includes a stagger angle distribution in accordance with one of TABLE III and TABLE IV, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.

### Claim 3 (depends on 1)

The rotor blade of claim 1, wherein the rotor blade forms part of a late stage of a compressor section.

### Claim 4 (depends on 1)

The rotor blade of claim 1, wherein the rotor blade is one of a nineteenth stage compressor rotor blade and a twentieth stage compressor rotor blade.

### Claim 5 (depends on 1)

The rotor blade of claim 1, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

### Claim 6 (depends on 1)

The rotor blade of claim 1, wherein the scaling factor is between about 0.01 inches and about 10 inches.

### Claim 7 (depends on 1)

The rotor blade of claim 1, wherein the X, Y and Z values in TABLE I are scalable as a function of a first constant or number to provide a first scaled-up or scaled-down airfoil, and wherein the X, Y and Z values in TABLE II are scalable as a function of a second constant or number to provide a second scaled-up or scaled-down airfoil.

### Claim 8

A rotor blade comprising:
an airfoil having a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define suction-side profile sections at each Z value, the suction-side profile sections at the Z values being joined smoothly with one another to form a complete airfoil suction-side shape.

### Claim 9 (depends on 8)

The rotor blade of claim 8, wherein the airfoil includes a stagger angle distribution in accordance with one of TABLE III and TABLE IV, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.

### Claim 10 (depends on 8)

The rotor blade of claim 8, wherein the rotor blade forms part of a late stage of a compressor section.

### Claim 11 (depends on 8)

The rotor blade of claim 8, wherein the rotor blade is one of a nineteenth stage compressor rotor blade and a twentieth stage compressor rotor blade.

### Claim 12 (depends on 8)

The rotor blade of claim 8, wherein the nominal suction-side profile lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

### Claim 13 (depends on 8)

The rotor blade of claim 8, wherein the scaling factor is between about 0.01 inches and about 10 inches.

### Claim 14 (depends on 8)

The rotor blade of claim 8, wherein the X, Y and Z values in TABLE I are scalable as a function of a first constant or number to provide a first scaled-up or scaled-down airfoil, and wherein the X, Y and Z values in TABLE II are scalable as a function of a second constant or number to provide a second scaled-up or scaled-down airfoil.

### Claim 15

A turbomachine comprising:
a compressor section;
a turbine section downstream from the compressor section;
a combustion section downstream from the compressor section and upstream from the turbine section; and
a rotor blade disposed within the compressor section of the turbomachine, the rotor blade comprising:
an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

### Claim 16 (depends on 15)

The turbomachine of claim 15, wherein the airfoil includes a stagger angle distribution in accordance with one of TABLE III and TABLE IV, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.

### Claim 17 (depends on 15)

The turbomachine of claim 15, wherein the rotor blade forms part of a late stage of the compressor section.

### Claim 18 (depends on 15)

The turbomachine of claim 15, wherein the rotor blade is one of a nineteenth stage compressor rotor blade and a twentieth stage compressor rotor blade.

### Claim 19 (depends on 15)

The turbomachine of claim 15, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

### Claim 20 (depends on 15)

The turbomachine of claim 15, wherein the scaling factor is between about 0.01 inches and about 10 inches.