Aerofoil array for a gas turbine with anti fluttering means

Patent metadata

Field	Value
Publication number	US-9650915-B2
Application number	US-201314407051-A
Country	US
Kind code	B2
Filing date	Jun 14, 2013
Priority date	Jun 14, 2012
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

An aerofoil array for a gas turbine system has an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow; the annular channel houses a plurality of aerofoils, arranged at a substantially constant angular pitch and comprising respective central portions and respective ends connected to the platforms; the aerofoils are formed by two series of aerofoils having a different geometrical feature in order to intentionally vary the eigenfrequencies and arranged about the longitudinal axis with a sequence that is regularly repeated all along the annular channel; even though the external geometry of the aerofoils is varied, the cross-sections remain unchanged in the central portions, at any given radius with respect to the longitudinal axis.

First claim

The invention claimed is:

1. An aerofoil array for a gas turbine system, the array comprising:
a) an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow;
b) a plurality of aerofoils, which are housed in said annular channel, are arranged at a substantially constant pitch about said longitudinal axis and are constituted by:
respective central portions,
respective outer radial ends, each defining a connecting portion that joins the corresponding central portion with said outer annular platform, and
respective inner radial ends, each defining a connecting portion that joins the corresponding central portion with said inner annular platform;

said aerofoils comprising first aerofoils and second aerofoils extending along first and, respectively, second directions, which are substantially radial with respect to said longitudinal axis; said second aerofoils having at least one different geometrical feature with respect to said first aerofoils, in order to intentionally vary the eigenfrequencies of the second aerofoils with respect to those of the first aerofoils said first and second aerofoils being arranged about said longitudinal axis with a sequence that is regularly repeated all along said annular channel;
on sectioning the central portions of said first and second aerofoils with a curved sectional surface corresponding to the theoretical trajectory of the gas flow at any given radius, with respect to said longitudinal axis, the cross-sections of said central portions are the same; said first and second directions defining the directions in which said cross-sections are stacked;
wherein said different geometrical feature is defined by the curvature and/or inclination of said second directions, with respect to the one of said first directions; the different curvature and/or inclination of said directions resulting in a translation of the cross sections so that some zones of the aerofoils have a slight shifting in the angular pitch and/or a slight staggering in the axial direction between the leading edges and between the trailing edges.

2. An array according to claim 1 , wherein said central portions have a radial extension equal to at least 60% of the radial height of said aerofoils.

3. An array according to claim 1 , further comprising a plurality of sectors, which are each made in a single piece and are equal to one another; each said sector comprising at least one of said first aerofoils and at least one of said second aerofoils.

4. An array according to claim 1 , wherein said aerofoils comprise third aerofoils, which have at least one further different geometrical feature with respect to said first and second aerofoils, in order to intentionally vary the eigenfrequencies of the third aerofoils with respect to those of the first and second aerofoils.

5. An array according to claim 4 , wherein the external geometry of said third aerofoils is intentionally different from that of said first and second aerofoils, without varying the cross-sections of the central portions of said first, second and third aerofoils, at any given radius with respect to said longitudinal axis.

6. An array according to claim 4 , wherein said third aerofoils have a rib arranged on the pressure side and parallel to a plane tangential to the gas flow path.

Assignees

• Ge Avio Srl

Inventors

• Calza Paolo
• Usseglio Matteo

Classifications

• F01D5/22

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title

• F01D25/06 Primary

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title