# US 11,441,427 B1 · Compressor rotor blade airfoils

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- Number: US 11,441,427 B1
- Document ID: US11441427B1
- Status: Granted
- Kind: B1
- Application number: 17/245,002
- Filed: 2021-04-30
- Granted: 2022-09-13
- Earliest claimed: 2021-04-30
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Paul G. Deivernois; Andrew Clifford Hart; Michael James Dutka; Jeremy Peter Latimer
- Web page: https://patentgrep.com/patent/US11441427B1

## CPC

- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F04D 29/324: {Blades}
- F04D 29/384: {characterised by form}
- F04D 29/544: {Blade shapes}
- F05D 2220/3217: for the first stage of a compressor or a low pressure compressor
- F05D 2240/124: related to the suction side of a stator vane
- F05D 2240/301: Cross-sectional characteristics
- F05D 2240/305: related to the pressure side of a rotor blade
- F05D 2240/306: related to the suction side of a rotor blade
- F05D 2250/38: angled, e.g. sweep angle
- F05D 2250/74: given by a set or table of xyz-coordinates
- Y02E 20/16: Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
- 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
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION

## 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 Table I. 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 are 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 Table I, 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 Table II, 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 an early stage of a compressor section of a turbomachine.

### Claim 4 (depends on 1)

The rotor blade of claim 1, wherein the rotor blade is disposed in one of a mid stage of a compressor section of a turbomachine or a late stage of the compressor section of the turbomachine.

### Claim 5 (depends on 1)

The rotor blade of claim 1, wherein the rotor blade is a first stage compressor rotor blade.

### Claim 6 (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 7 (depends on 1)

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

### Claim 8 (depends on 1)

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

### Claim 9

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 Table I, 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 10 (depends on 9)

The rotor blade of claim 9, wherein the airfoil includes a stagger angle distribution in accordance with Table II, 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 11 (depends on 9)

The rotor blade of claim 9, wherein the rotor blade forms part of an early stage of a compressor section of a turbomachine.

### Claim 12 (depends on 9)

The rotor blade of claim 9, wherein the rotor blade is disposed in one of a mid stage of a compressor section of a turbomachine or a late stage of the compressor section of the turbomachine.

### Claim 13 (depends on 9)

The rotor blade of claim 9, wherein the rotor blade is a first stage compressor rotor blade.

### Claim 14 (depends on 9)

The rotor blade of claim 9, 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 15 (depends on 9)

The rotor blade of claim 9, wherein the scaling factor is between about 0.01 inches and about 10 inches.

### Claim 16 (depends on 9)

The rotor blade of claim 9, wherein the X, Y and Z values are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

### Claim 17

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
two or more rotor blades disposed within the compressor section of the turbomachine, each rotor blade of the two or more rotor blades 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 Table I, 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 height 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 18 (depends on 17)

The turbomachine of claim 17, wherein the airfoil includes a stagger angle distribution in accordance with Table II, 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 19 (depends on 17)

The turbomachine of claim 17, wherein the two or more rotor blades each form part of an early stage of the compressor section.

### Claim 20 (depends on 17)

The turbomachine of claim 17, wherein each rotor blade of the two or more rotor blades is disposed in a first stage of the compressor section.