# US 11,306,735 B2 · Turbine nozzle airfoil profile

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- Number: US 11,306,735 B2
- Document ID: US11306735B2
- Status: Granted
- Kind: B2
- Application number: 16/654,496
- Filed: 2019-10-16
- Published: 2021-04-22
- Granted: 2022-04-19
- Earliest claimed: 2019-10-16
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Sylvain Pierre; Brendon James Leary; Jason Adam Neville
- Web page: https://patentgrep.com/patent/US11306735B2

## CPC

- F04D 29/441: {especially adapted for elastic fluid pumps}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F01D 5/142: {of the blades of successive rotor or stator blade-rows}
- F01D 5/326: {Locking of axial insertion type blades by other means}
- F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045})
- F04D 29/266: {mounting compressor rotors on shafts}
- F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F05D 2220/3212: the first stage of a turbine
- F05D 2240/123: related to the pressure side of a stator vane
- F05D 2240/124: related to the suction side of a stator vane
- F05D 2240/301: Cross-sectional characteristics
- F05D 2250/74: given by a set or table of xyz-coordinates
- 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)
- 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 turbine nozzle includes an airfoil shape. The airfoil shape may have 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 in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

## Claims

### Claim 1

A turbine nozzle comprising an airfoil having an airfoil shape, the airfoil extending between a root and a tip and between a leading edge and a trailing edge, the airfoil shape having a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, Z having a point data origin defined at the root at the leading edge 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 in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

### Claim 2 (depends on 1)

The turbine nozzle of claim 1, wherein the turbine nozzle forms part of a stage of a turbine.

### Claim 3 (depends on 1)

The turbine nozzle of claim 1, wherein the turbine nozzle is a first stage turbine nozzle.

### Claim 4 (depends on 1)

The turbine nozzle 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 5 (depends on 1)

The turbine nozzle of claim 1, wherein a height of the turbine nozzle is 2 inches to 50 inches.

### Claim 6 (depends on 1)

The turbine nozzle of claim 1, wherein the X, Y and Z distances are scalable as a function of a constant or number to provide a scaled-up or scaled-down airfoil.

### Claim 7

A turbine nozzle comprising an airfoil having a suction-side uncoated nominal airfoil profile, the airfoil extending between a root and a tip and between a leading edge and a trailing edge, the uncoated nominal suction-side profile 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, Z having a point data origin defined at the root at the leading edge 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 in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete suction-side airfoil shape, the X, Y and Z distances being scalable as a function of a constant or number to provide a scaled-up or scaled-down airfoil.

### Claim 8 (depends on 7)

The turbine nozzle of claim 7, wherein the turbine nozzle forms part of a stage of a turbine.

### Claim 9 (depends on 7)

The turbine nozzle of claim 7, wherein the turbine nozzle is a first stage turbine nozzle.

### Claim 10 (depends on 7)

The turbine nozzle of claim 7, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

### Claim 11 (depends on 7)

The turbine nozzle of claim 7, wherein a height of the turbine nozzle is 2 inches to 50 inches.

### Claim 12

A turbine comprising a plurality of turbine nozzles, each of the turbine nozzles comprising an airfoil having an airfoil shape, the airfoil extending between a root and a tip and between a leading edge and a trailing edge, the airfoil having a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, Z having a point data origin defined at the root at the leading edge 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 in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

### Claim 13 (depends on 12)

The turbine of claim 12, wherein the plurality of turbine nozzles forms part of a stage of a turbine.

### Claim 14 (depends on 12)

The turbine of claim 12, wherein the plurality of turbine nozzles comprises a plurality of first stage turbine nozzles.

### Claim 15 (depends on 12)

The turbine of claim 12, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

### Claim 16 (depends on 12)

The turbine of claim 12, wherein a height of the turbine nozzle is 2 inches to 50 inches.

### Claim 17 (depends on 12)

The turbine of claim 12, wherein the X, Y and Z distances are scalable as a function of a constant or number to provide a scaled-up or scaled-down airfoil.

### Claim 18 (depends on 12)

The turbine of claim 12, wherein X represents a distance parallel to a turbine axis of rotation.