Impingement cooling of turbine blades or vanes

Patent metadata

Field	Value
Publication number	US-9777581-B2
Application number	US-201214343855-A
Country	US
Kind code	B2
Filing date	Sep 3, 2012
Priority date	Sep 23, 2011
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity, and at least a first impingement device arrangeable within the cavity. The at least first impingement device is self-locking, resilient and preloadable and has at least one locking element to lock the at least first impingement device in place in the cavity via a force fit between the at least one locking element and the inner wall of the cavity wherein the locking element of the at least first impingement device is embodied as a protrusion extending in an assembled state of the at least first impingement device in the cavity basically perpendicular to a surface of a side wall of the at least first impingement device in a direction towards the inner wall.

First claim

The invention claimed is:

1. A turbine assembly comprising
an aerofoil, comprising a cavity with an inner wall and comprising an aperture providing access to the cavity, and
a first impingement device arrangeable within the cavity,
wherein the first impingement device is self-locking, resilient and preloadable and comprises two locking elements to lock the first impingement device in place in the cavity via a force fit between each one of the two locking elements and the inner wall of the cavity wherein
the first impingement device comprises at least two side walls with
the two locking elements of the first impingement device are embodied as protrusions each processed by a bending of an end region of the side walls with an angle of 90°+/−30° to a surface of each side wall, wherein the surface faces the inner wall and is arranged in parallel to the inner wall, therefore each protrusion extends in an assembled state of the first impingement device in the cavity with an angle of 90°+/−30° to the surface of each side wall of the first impingement device towards the inner wall,
the turbine assembly further comprising a second impingement device disposed in the cavity, the second impingement device comprising an outer wall comprising upstream impingement holes configured to inject cooling medium as jets towards the inner wall for impingement at an upstream impingement area of the inner wall,
wherein the aerofoil is configured to direct the cooling medium into the second impingement device, and then to direct the cooling medium previously injected as jets from the second impingement device into the first impingement device.

2. The turbine assembly according to claim 1 , wherein
the inner wall comprises a locking structure and
wherein each locking element of the first impingement device and a respective locking structure of the inner wall engage with each other via a form fit.

3. The turbine assembly according to claim 2 , wherein
the locking structure of the inner wall is embodied as a recess extending perpendicular to an inner surface of the inner wall.

4. The turbine assembly according to claim 2 , further comprising:
at least one of vertically oriented spacers and horizontally oriented spacers in an inner wall of the aerofoil configured to hold the first impingement device at a predetermined distance from the inner wall; and
recesses in the spacers,
wherein the locking structures comprises the recesses.

5. The turbine assembly according to claim 1 , wherein
the first impingement device is built from a metal sheet.

6. The turbine assembly according to claim 1 , wherein
in the assembled state of the first impingement device in the cavity, the at least two side walls are arranged in an acute angle towards each other.

7. The turbine assembly according to claim 1 , further comprising
a platform arranged perpendicular to a span wise direction of the aerofoil and covering the aperture at least partially, and comprising a gap arranged between the platform and the first impingement device,
wherein a sealing element seals the gap between the platform and the first impingement device at least partially.

8. The turbine assembly according to claim 1 , wherein
the first impingement device comprises a first outer wall,
wherein the first outer wall comprises impingement holes for injecting cooling medium, which is fed through the aperture, as jets towards the inner wall for impingement at an impingement area of the inner wall.

9. The turbine assembly according to claim 1 , further comprising
a clearance element, which is arranged at or in the first impingement device to provide a bypass which inhibits the cooling medium to eject through impingement holes of the first impingement device.

10. The turbine assembly according to claim 1 , further comprising
an aperture in the second impingement device,
wherein the aperture provides an upstream bypass located upstream of the first impingement device which inhibits the cooling medium to eject through the upstream impingement holes and which aims the cooling medium into the first impingement device.

11. The turbine assembly according to claim 1 , wherein
the first impingement device is arranged in a part of the cavity which is oriented towards a trailing edge of the aerofoil and the second impingement device is arranged in a part of the cavity which is oriented towards a leading edge of the aerofoil.

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

13. The turbine assembly according to claim 1 , wherein
the first impingement device comprises at least two side walls, which, in the assembled state of the first impingement device in the cavity, are arranged in an acute angle towards each other with an angle of 5° to 45°.

14. The turbine assembly according to claim 1 , wherein
the first impingement device comprises at least two side walls, which, in the assembled state of the first impingement device in the cavity, are arranged in an acute angle towards each other with an angle of about 15°.

15. The turbine assembly according to claim 1 , further comprising at least one of vertically oriented spacers and horizontally oriented spacers in an inner wall of the aerofoil.

16. The turbine assembly according to claim 1 , further comprising at least one of vertically oriented spacers and horizontally oriented spacers in an inner wall of the aerofoil configured to hold the first impingement device at a predetermined distance from the inner wall.

17. The turbine assembly according to claim 1 , wherein the bends are outward, wherein the angle is 90°, wherein each protrusion comprises opposite surfaces and an end surface spanning the opposite surfaces, and wherein each end surface abuts the inner wall.

18. A method for assembling an impingement device in a cavity of an aerofoil of a turbine assembly according to claim 1 , the method comprising:
preloading the impingement device in a form for insertion;
inserting the impingement device through an aperture in a platform of the aerofoil into the cavity;
maneuvering of the impingement device rearward toward a trailing edge of the airfoil and into position inside the cavity and under the platform;
relaxing the impingement device so that two locking elements of the impingement device, each being embodied as a protrusion and being each processed by a bending of an end region of one of the two side walls of the impingement device with an angle of 90°+/−30° to a surface of each side wall, wherein the surface faces an inner wall of the cavity and is arranged in parallel to the inner wall, establish a force fit between the two locking elements and the inner wall of the cavity with each protrusion extending with an angle of 90°+/−30° to the surface of each side wall of the first impingement device in a direction towards the inner wall;
locking the impingement device in the cavity into position thereby, and
inserting a second impingement device into the cavity, the second impingement device comprising an outer wall comprising upstream impingement holes configured to inject cooling medium as jets towards the inner wall for impingement at an upstream impingement area of the inner wall,
wherein the aerofoil is configured to direct the cooling medium injected as jets from the second impingement device into the first impingement device.

19. A turbine assembly comprising
an aerofoil, comprising: a cavity; an aperture providing access to the cavity; and an inner wall comprising locking structures, an

Assignees

• Nilsson Ulf
• Siemens Ag

Inventors

• Nilsson Ulf

Classifications

• Y10T29/49872

  Confining elastic part in socket · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• B23P11/02

  by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits · 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