Turbine blade

• US 7,654,795 B2
• Filed: 11/02/2006
• Issued: 02/02/2010
• Est. Priority Date: 12/03/2005
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Tibbott, Ian
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/591,615
• Publication Number:
  US 20090081024A1
• Time in Patent Office: 1,188 Days
• Field of Search: 415/115, 415/121.1, 415/121.2, 415/121.3, 415/169.1, 416/92, 416/96.R, 416/97.R, 416/97.A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Abstract

An aerofoil for a gas turbine engine, the aerofoil comprises a leading edge and a trailing edge, pressure and suction surfaces and defines therebetween an internal passage for the flow of cooling fluid therethrough. A particle deflector means is disposed within the passage to deflect particles within a cooling fluid flow away from a region of the aerofoil susceptible to particle buildup and subsequent blockage, such as a cooling passage for a shroud of a blade.

Claims

1. An aerofoil for a gas turbine engine, the aerofoil comprising:

a leading edge; and

a trailing edge;

pressure and suction surfaces; and

defines therebetween an internal passage for a flow of cooling fluid therethrough, wherein

the internal passage contains a particle deflector to deflect particles within the flow of cooling fluid away from a region of the aerofoil susceptible to particle buildup and subsequent blockage, wherein

the region of the aerofoil susceptible to particle buildup and subsequent blockage is a cooling hole defined in the aerofoil, wherein

the aerofoil comprises a shroud portion, wherein the shroud portion defines the cooling hole.

2. An aerofoil for a gas turbine engine, the aerofoil comprising:

a leading edge; and

a trailing edge;

pressure and suction surfaces; and

defines therebetween an internal passage for a flow of cooling fluid therethrough, wherein

the internal passage contains a particle deflector to deflect particles within the flow of cooling fluid away from a region of the aerofoil susceptible to particle build up and subsequent blockage, wherein

the region of the aerofoil susceptible to particle buildup and subsequent blockage is a cooling hole defined in the aerofoil, wherein

the entry to the cooling hole is nearer the leading edge than an entry to a dust hole.

3. An aerofoil for a gas turbine engine, the aerofoil comprising:

a leading edge; and

a trailing edge;

pressure and suction surfaces; and

defines therebetween an internal passage for a flow of cooling fluid therethrough, wherein

the internal passage contains a particle deflector to deflect particles within the flow of cooling fluid away from a region of the aerofoil susceptible to particle build up and subsequent blockage, wherein

the aerofoil comprises at least one radially extending fin mounted on a radially outer part of the aerofoil.

4. An aerofoil as claimed in claim 3, wherein

an outlet of a cooling hole is downstream of the at least one radially extending fin.

5. An aerofoil as claimed in claim 3, wherein

an outlet of a dust hole is downstream of at least one radially extending fin.