# US 10,480,324 B2 · Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the third stage of a turbine

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- Number: US 10,480,324 B2
- Document ID: US10480324B2
- Status: Granted
- Kind: B2
- Application number: 15/393,498
- Filed: 2016-12-29
- Published: 2018-08-16
- Granted: 2019-11-19
- Earliest claimed: 2016-07-13
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Pascal Pierre Routier; Laurent Patrick Coudert; Maxime Didier Delabriere; Jean-Armand Marc Destouches
- Web page: https://patentgrep.com/patent/US10480324B2

## CPC

- F01D 5/142: {of the blades of successive rotor or stator blade-rows}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 9/047: {Nozzle boxes}
- F05D 2220/3218: for an intermediate stage of a compressor
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2240/128: Nozzles
- F05D 2250/71: curved
- F05D 2250/74: given by a set or table of xyz-coordinates
- 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

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

## Claims

### Claim 1

A turbine vane configured to be mounted to a turbine and presenting an aerodynamic profile, comprising: the aerodynamic profile, defining the turbine vane when cold and in a non-coated state, the aerodynamic profile being identical to a nominal profile determined by Cartesian coordinates X,Y,Zadim given in Table 1, in which coordinate Zadim is a quotient D/H, where D is a distance of a point under consideration from a reference X,Y plane situated at a base of the nominal profile, and H is a height of said nominal profile measured from said reference X,Y plane out to an end of the vane, the measurements D and H being taken radially relative to an axial direction of the turbine vane, while the coordinate X is measured in the axial direction of the turbine vane.

### Claim 2 (depends on 1)

The turbine vane as claimed in claim 1, wherein the vane is a nozzle vane forming a part of a stator of a turbine.

### Claim 3 (depends on 2)

The turbine vane as claimed in claim 2, wherein the nozzle vane is of a third stage of the turbine.

### Claim 4 (depends on 2)

The turbine vane as claimed in claim 2, wherein the vane is usable in a third stage nozzle of the turbine, the turbine containing seven stages.

### Claim 5 (depends on 1)

A turbine, including a plurality of turbine vanes as claimed in claim 1.

### Claim 6 (depends on 5)

The turbine as claimed in claim 5, including a nozzle that is stationary during operation, wherein the plurality of turbine vanes includes 140 to 160 turbine vanes.

### Claim 7 (depends on 1)

A turbine nozzle forming a portion of a turbine stator, further comprising a plurality of turbine vanes as claimed in claim 1.

### Claim 8 (depends on 7)

The turbine nozzle as claimed in claim 7, wherein the plurality of turbine vanes includes 140 to 160 turbine vanes.