Airfoil device for a gas turbine and corresponding arrangement

Patent metadata

Field	Value
Publication number	US-10323531-B2
Application number	US-201415100889-A
Country	US
Kind code	B2
Filing date	Nov 11, 2014
Priority date	Dec 9, 2013
Publication date	Jun 18, 2019
Grant date	Jun 18, 2019

Abstract

An airfoil device for a gas turbine has a root section mountable to an airfoil disc and an airfoil element. The root section has a platform at which the airfoil element is arranged. The root section has a cavity surrounded by an inner surface of the platform, a first and a second edge side of the root section. A seal strip is arranged at the inner surface, wherein the first edge side has a recess into which a first end section of the seal strip is arranged. The root section has a supporting lever extending from the second edge side into the cavity. The supporting lever is formed such that a further cavity is formed between the inner surface, the second edge side and the supporting lever, wherein the second end section of the seal strip is arranged inside the further cavity.

First claim

The invention claimed is:

1. An airfoil device for a gas turbine, the airfoil device comprising:
a root section which is mountable to an airfoil disc of the gas turbine,
an airfoil element,
wherein the root section comprises a platform at which the airfoil element is arranged, wherein the root section comprises a cavity which is surrounded by a radially inner surface of the platform, a first edge side of the root section and a second edge side of the root section,
wherein the first edge side and the second edge side are spaced apart from each other along an axial direction of the gas turbine, and
a seal strip which is arranged at the inner surface,
wherein the seal strip comprises a first end section, a middle section and a second end section,
wherein the first end section is spaced apart from the second end section along the axial direction and the middle section is arranged between the first end section and the second end section,
wherein the first edge side comprises a recess into which the first end section of the seal strip is inserted such that the recess surrounds the first end section and fixes the first end section to the inner surface,
wherein the root section comprises a supporting lever extending from the second edge side into the cavity such that a free end of the supporting lever forms a contact region with the middle section of the seal strip for fixing the middle section of the seal strip to the inner surface,
wherein the supporting lever is further formed such that a further cavity is formed between the inner surface, the second edge side and the supporting lever,
wherein the second end section of the seal strip is arranged inside the further cavity, and
wherein the second edge side comprises a seal strip inlet fully through the second edge side configured to permit the seal strip to pass through the second edge side and move in the axial direction to enable installation and removal of the first end section into the recess in the first edge side.

2. The airfoil device according to claim 1 ,
wherein a first part of the middle section of the seal strip between the contact region and the first end section is arranged inside the cavity, wherein the second end section and a second part of the middle section of the seal strip between the contact region and the second end section is arranged inside the further cavity.

3. The airfoil device according to claim 1 ,
wherein the supporting lever is formed such that a first axial length of the seal strip between the contact region and the first end section is larger than a second axial length of the seal strip between the contact region and the second end section.

4. The airfoil device according to claim 1 ,
wherein the seal strip inlet is formed such that air is streamable out of the further cavity.

5. The airfoil device according to claim 1 ,
wherein the second edge side comprises a stopper section which is formed such that the second end section of the seal strip abuts against the stopper section.

6. The airfoil device according to claim 1 ,
wherein the first edge side is a trailing edge side of the root section, and
wherein the second edge side is a leading edge side of the root section.

7. An airfoil arrangement for a gas turbine, the airfoil arrangement comprising
an airfoil device according to claim 1 , and
a further airfoil device according to claim 1 ,
wherein the airfoil device and the further airfoil device are arranged one after another along a circumferential direction of the gas turbine,
wherein the seal strip is formed such that the seal strip extends between the airfoil device and the further airfoil device for sealing a gap between the airfoil device and the further airfoil device.

8. The airfoil device according to claim 5 , wherein the stopper section is disposed immediately radially outward of the seal strip inlet.

9. An airfoil device for a gas turbine, the airfoil device comprising:
an airfoil element,
a root section which is mountable to an airfoil disc of the gas turbine, comprising: a platform at which the airfoil element is arranged; a cavity which is surrounded by a radially inner surface of the platform; a first edge side of the root section; and a second edge side of the root section,
wherein the first edge side and the second edge side are spaced apart from each other along an axial direction of the gas turbine, and
a seal strip which is arranged at the radially inner surface, comprising: a first end section; a middle section; and a second end section, wherein the first end section is spaced apart from the second end section along the axial direction, and wherein the middle section is arranged between the first end section and the second end section,
wherein the first edge side comprises a recess into which the first end section of the seal strip is inserted such that the recess surrounds the first end section and fixes the first end section to the radially inner surface,
wherein the root section comprises a supporting lever that extends into the cavity such that a free end of the supporting lever forms a contact region with the middle section of the seal strip for fixing the middle section of the seal strip to the radially inner surface,
wherein the supporting lever extends along the axial direction from a leading edge of the platform toward a trailing edge of the platform, and is inclined such that a trailing end of the supporting lever is closer to the platform than a leading end of the supporting lever,
wherein the supporting lever is further formed such that a further cavity is formed between the radially inner surface, the second edge side and the supporting lever, and
wherein the second end section of the seal strip is arranged inside the further cavity.

Assignees

• Siemens Ag

Inventors

• Bluck Richard
• Overton David

Classifications

• F01D11/008 Primary

  by spacer elements between the blades, e.g. independent interblade platforms · CPC title

• F01D11/006 Primary

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title