Impingement cooling of turbine blades or vanes

Patent metadata

Field	Value
Publication number	US-10012093-B2
Application number	US-201214373861-A
Country	US
Kind code	B2
Filing date	Nov 22, 2012
Priority date	Feb 9, 2012
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

A turbine assembly is provided having a hollow aerofoil having a cavity with an impingement tube insertable inside the cavity and used for impingement cooling of an inner surface of the cavity, and a platform arranged at a radial end of the hollow aerofoil, and a cooling chamber used for cooling of the platform which is arranged relative to the hollow aerofoil on an opposed side of the platform. The cooling chamber is limited at a first radial end from the platform and at an opposed radial second end from a cover plate. The impingement tube is formed from a leading piece and a trailing piece. The leading piece extends in span wise direction at least completely through the cooling chamber from the platform to the cover plate and the trailing piece terminates in span wise direction at the platform.

First claim

The invention claimed is:

1. A turbine assembly comprising:
an aerofoil extending in a radial direction from a platform;
an impingement tube extending in the radial direction through a cavity formed in the aerofoil, the impingement tube comprising a leading piece located toward a leading edge of the aerofoil and a trailing piece located toward a trailing edge of the aerofoil;
a platform cooling chamber;
a first cooling medium flow path arranged to direct a first cooling medium into the leading piece; and
a second cooling medium flow path arranged to direct a second cooling medium into the trailing piece upon exiting the platform cooling chamber;
wherein the aerofoil extends in the radial direction between an inner platform and an outer platform, and wherein the turbine assembly comprises both an inner platform cooling chamber and an outer platform cooling chamber, and further comprising:
the second cooling medium flow path is arranged to direct a first portion of the second cooling medium through the inner platform cooling chamber then into the trailing piece and a second portion of the second cooling medium through the outer platform cooling chamber then into the trailing piece.

2. The turbine assembly according to claim 1 , wherein the leading piece of the impingement tube ends at the cover plate in a hermetically sealed manner.

3. The turbine assembly according to claim 1 , wherein the impingement tube extends substantially completely through a span of the aerofoil.

4. The turbine assembly according to claim 1 , wherein the leading piece and the trailing piece of the impingement tube both terminate at the inner platform.

5. The turbine assembly according to claim 4 , wherein the leading piece and the trailing piece of the impingement tube both terminate at the inner platform in a radial direction flush with each other.

6. The turbine assembly according to claim 1 , wherein the trailing edge has exit apertures to allow cooling medium to exit the aerofoil.

7. The turbine assembly according to claim 1 , wherein the aerofoil is a turbine blade or vane.

8. The turbine assembly according to claim 1 wherein the leading piece and the trailing piece are arranged side by side in an axial direction.

9. A gas turbine engine comprising a plurality of turbine assemblies, wherein at least one of the turbine assemblies is arranged according to claim 1 .

10. The turbine assembly of claim 1 , further comprising an aperture formed in the leading piece and a corresponding aperture formed in the trailing piece operable to allow a flow communication of cooling medium between the leading and trailing pieces.

11. The turbine assembly of claim 1 , further comprising:
the leading piece extends at its respective radial ends through the inner platform cooling chamber and the outer platform cooling chamber, and
the first cooling medium flow path comprises a respective inlet for the first cooling medium at each radial end of the leading piece.

12. The turbine assembly of claim 1 , further comprising:
the leading piece extends at one end through one of the inner platform cooling chamber and the outer platform cooling chamber; and
the first cooling medium flow path comprises an inlet for the first cooling medium at the one end of the leading piece.

13. The turbine assembly of claim 1 , wherein the leading piece extends at an inner radial end through the inner platform cooling chamber; and
the first cooling medium flow path comprises an inlet for the first cooling medium at the inner radial end of the leading piece.

14. The turbine assembly of claim 1 , wherein the leading piece extends at its respective inner and outer radial ends through the respective inner and outer platform cooling chambers; and
the first cooling medium flow path comprises an inlet for the first cooling medium at both the inner and outer radial ends of the leading piece.

15. A turbine assembly comprising:
an aerofoil comprising a first cavity;
an impingement tube inserted inside the first cavity for impingement cooling of an inner surface of the cavity;
a platform at a first radial end of the aerofoil;
a cooling chamber disposed on an opposed side of the platform relative to the aerofoil, the cooling chamber defined at a first radial end by the platform and at an opposed second radial end by a cover plate;
wherein the impingement tube comprises a leading piece and a trailing piece both being inserted in said first cavity, wherein the leading piece is located towards a leading edge of the aerofoil and the trailing piece is located towards a trailing edge of the aerofoil; and
wherein the leading piece of the impingement tube extends in a radial direction completely through the cooling chamber from the platform to the cover plate and wherein the trailing piece of the impingement tube terminates in the radial direction at the platform;
the turbine assembly arranged to be cooled by a first stream of cooling medium which is fed to the leading piece of the impingement tube and by a second stream of cooling medium which is fed first to the cooling chamber and thereafter to the trailing piece of the impingement tube in series.

16. The turbine assembly according to claim 15 , further comprising a further platform at a second radial end of the aerofoil, and wherein the leading piece and the trailing piece of the impingement tube both terminate at the further platform.

17. The turbine assembly of claim 15 , further comprising an aperture allowing a flow communication of cooling medium between the leading and trailing pieces.

Assignees

• Siemens Ag

Inventors

• Mugglestone Jonathan

Classifications

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F05D2220/31

  in steam turbines · CPC title