Turbine vane hollow inner rail

Patent metadata

Field	Value
Publication number	US-9869200-B2
Application number	US-201113642881-A
Country	US
Kind code	B2
Filing date	Mar 30, 2011
Priority date	Apr 29, 2010
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A guide vane device for a turbine has an inner platform with a through hole forming a fluid channel for a cooling fluid, wherein the inner platform extends in a circumferential direction around a shaft of the turbine. The guide vane device further includes a hollow aerofoil with a cooling opening for exchanging the cooling fluid passing the through hole into or from the hollow aerofoil, wherein the hollow aerofoil is fixed to a first surface of the inner platform, and a rail with a recess with a cooling fluid passage forming a passage for the cooling fluid to the through hole, wherein the rail is fixed to a second surface of the inner platform and the rail extends along the second surface in the circumferential direction around the shaft. The cooling fluid passage has in the circumferential direction at least the dimension of the through hole.

First claim

The invention claimed is:

1. Guide vane device for a turbine, the guide vane device comprising:
an inner platform having a body defining a through hole through which a cooling fluid flows, wherein the inner platform extends in a circumferential direction around a shaft of a turbine,
an aerofoil having sidewalls defining a cavity in fluid communication with the through hole, wherein the aerofoil is fixed to a first surface of the inner platform,
a rail comprising a recessed portion extending in the circumferential direction and having a cooling fluid passage formed in the recessed portion and extending from the recessed portion through a body of the rail, the cooling fluid passage overlapping a cross-section of the through hole such that the cooling fluid flows through the cooling fluid passage, the through hole, and into the cavity, wherein the rail is fixed to a second surface of the inner platform and the rail extends along the second surface in the circumferential direction around the shaft, and
wherein the cooling fluid passage comprises in the circumferential direction at least the dimension of the through hole;
a further aerofoil fixed to the surface of the inner platform and in flow communication with the through hole,
wherein the inner platform comprises a further through hole for flow of the cooling fluid there through,
wherein the rail comprises a further recessed portion comprising a further cooling fluid passage formed therein for the cooling fluid to flow through the further cooling fluid passage and to the further through hole, and
wherein the further cooling flow passage comprises in circumferential direction at least the dimension of the further through hole.

2. The guide vane device of claim 1 , wherein the cooling fluid passage has a larger cross-sectional area than the through hole.

3. The guide vane device of claim 1 , wherein the rail is integrally formed with the platform.

4. The guide vane device of claim 1 , wherein the aerofoil is integrally formed with the inner platform.

5. The guide vane device of claim 1 , further comprising:
an outer platform to which the aerofoil is attached at an outer end of the aerofoil.

Assignees

• Jones Richard
• Pacey Andy
• Siemens Ag

Inventors

• Jones Richard
• Pacey Andy

Classifications

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D9/047

  Nozzle boxes · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title