Method for making a shaped turbine aerofoil

Patent metadata

Field	Value
Publication number	US-9506348-B2
Application number	US-201214355983-A
Country	US
Kind code	B2
Filing date	Nov 2, 2012
Priority date	Nov 3, 2011
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.

First claim

The invention claimed is:

1. A method for making a turbine aerofoil starting from a reference aerofoil, comprising the steps of:
a) establishing five zones along a trailing edge of the turbine aerofoil with a zone 1 comprising 0-10% thereof, a zone 2 comprising 10-25% thereof, a zone 3 comprising 25-75% thereof, a zone 4 comprising 75-90% thereof, and a zone 5 comprising 90-100% thereof;
b) locally reducing the metallic exit angle at the trailing edge with respect to the areas of zones 2 and 4 which correspond substantially, in use, to the position of the peaks of the secondary flows in the boundary layer; and
c) increasing the metallic exit angle in the remaining areas of zones 1, 3 and 5 the trailing edge, with respect to that of the reference aerofoil, so as to substantially restore the same average value of the metallic exit angle of the reference aerofoil.

2. The method according to claim 1 wherein the reduction of the metallic exit angle in zones 2 and 4 is less than or equal to 2°.

3. The method according claim 1 , wherein said reference aerofoil is defined by an aerofoil in which a load along a height of the aerofoil varies with a linear or parabolic law along the height of the aerofoil.

4. The method according claim 1 , wherein a load along a height of the aerofoil varies along the height of the aerofoil with a fourth degree polynomial law.

5. A method for making a turbine aerofoil starting from a reference aerofoil, comprising the steps of:
a) establishing five zones along a height of a trailing edge of the turbine aerofoil with a zone 1 comprising 0-10% thereof, a zone 2 comprising 10-25% thereof, a zone 3 comprising 25-75% thereof, a zone 4 comprising 75-90% thereof, and a zone 5 comprising 90-100% thereof;
b) modifying each metallic exit angle along the area of each of zones 1-5 to be increased or reduced relative to a metallic exit angle of the reference aerofoil; and
c) creating the metallic exit angle at the trailing edge with respect to the areas of zones 2 and 4 which correspond substantially, in use, to the position of the peaks of the secondary flows in the boundary layer, to be opposite to the modification of the metallic exit angle being made along zones 1, 3 and 5 of the turbine aerofoil.

6. The method for making a turbine aerofoil as in claim 5 further including the steps of:
reducing the metallic exit angle in zones 2 and 4, and increasing the metallic exit angle in zones 1, 3 and 5.

Assignees

• Ge Avio Srl

Inventors

• Bertini Francesco

Classifications

• F05D2230/00

  Manufacture · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• Y10T29/49336

  Blade making · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title