Turbine assembly for impingement cooling and method of assembling

Patent metadata

Field	Value
Publication number	US-10995622-B2
Application number	US-201816619632-A
Country	US
Kind code	B2
Filing date	Jun 14, 2018
Priority date	Jun 29, 2017
Publication date	May 4, 2021
Grant date	May 4, 2021

Abstract

A turbine assembly having a hollow aerofoil, an impingement tube, and an impingement tube sleeve. The sleeve has as least one impingement tube sleeve segment, the aerofoil having at its interior surface longitudinal ribs extending from a leading edge towards a trailing edge. A first impingement tube sleeve segment provides a slotted flow blocker at a surface of the first impingement tube sleeve segment, the first impingement tube sleeve segment inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the first impingement tube sleeve segment rests on the ribs. The impingement tube is inserted into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.

First claim

The invention claimed is:

1. A turbine assembly, comprising:
a basically hollow aerofoil, an impingement tube, and an impingement tube sleeve, the impingement tube sleeve comprising at least one impingement tube sleeve segment, the hollow aerofoil having at its interior surface longitudinal ribs extending from a leading edge towards a trailing edge of the hollow aerofoil,
wherein a first impingement tube sleeve segment of the at least one impingement tube sleeve segment provides a slotted flow blocker at a surface of the first impingement tube sleeve segment, the first impingement tube sleeve segment being inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the first impingement tube sleeve segment rests on the ribs,
wherein the impingement tube is inserted into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.

2. The turbine assembly according to claim 1 ,
wherein a plurality of impingement cooling cavities are formed between the interior surface of the hollow aerofoil and surfaces of the at least one impingement tube sleeve segment, each separated by one of the ribs.

3. The turbine assembly according to claim 1 ,
wherein a second impingement tube sleeve segment of the at least one impingement tube sleeve segment provides a slotted flow blocker at a surface of the second impingement tube sleeve segment, the second impingement tube sleeve segment being inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the second impingement tube sleeve segment rests on the ribs,
wherein the slotted flow blocker of the first impingement tube sleeve segment and the slotted flow blocker of the second impingement tube sleeve segment define impingement cooling cavities for a leading edge of the aerofoil which are separated by the flow blockers from remaining impingement cooling cavities.

4. The turbine assembly according to claim 1 ,
wherein the at least one impingement tube sleeve segment and the impingement tube are joined via a form-fit connection.

5. The turbine assembly according to claim 1 ,
wherein the first impingement tube sleeve segment comprises cut-outs wherein impingement cooling holes of the impingement tube are positioned in alignment of the cut-outs.

6. The turbine assembly according to claim 1 ,
wherein the slotted flow blocker is arranged as a slotted ridge attached to or being part of the first impingement tube sleeve segment, or as folded sheet metal cut-outs of the first impingement tube sleeve segment.

7. The turbine assembly according to claim 1 ,
wherein the slotted flow blocker is arranged as broken seal elements attached to the first impingement tube sleeve segment, or configured as rope seal elements.

8. The turbine assembly according to claim 1 ,
wherein the slotted flow blocker extends substantially in span-wise direction of the first impingement tube sleeve segment.

9. The turbine assembly according to claim 1 ,
wherein the hollow aerofoil, the impingement tube and the impingement tube sleeve are separate components joined together for the turbine assembly, and/or
wherein the impingement tube and the impingement tube sleeve comprise sheet metal inserts for the hollow aerofoil.

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

11. A method for assembling a turbine assembly according to claim 1 , wherein the method comprises:
providing the basically hollow aerofoil;
inserting the first impingement tube sleeve segment into a central region of the hollow aerofoil;
manoeuvring the inserted first impingement tube sleeve segment into position in a direction of a corresponding wall section of the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker of the first impingement tube sleeve segment and such that the surface of the first impingement tube sleeve segment rests on the ribs of the hollow aerofoil;
optionally inserting and manoeuvring at least one further one of the at least one impingement tube sleeve segment such that a further surface of the at least one further one of the at least one impingement tube sleeve segment rests on the ribs of the hollow aerofoil;
inserting the impingement tube into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.

12. The method for assembling a turbine assembly according to claim 11 ,
wherein inserting first impingement tube sleeve segment into a central region of the hollow aerofoil and inserting the impingement tube into the hollow aerofoil are performed by bringing the respective component into the hollow aerofoil via an aperture from a span-wise direction.

Assignees

• Siemens Ag
• Siemens Energy Global Gmbh & Co Kg

Inventors

• Mugglestone Jonathan

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F05D2230/60

  Assembly methods · CPC title