Gas turbine rotor blade and gas turbine rotor

Patent metadata

Field	Value
Publication number	US-9909439-B2
Application number	US-201414763727-A
Country	US
Kind code	B2
Filing date	Jan 14, 2014
Priority date	Feb 1, 2013
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.

First claim

The invention claimed is:

1. A gas turbine rotor blade including a root portion, a platform and an airfoil portion arranged along a span direction of the rotor blade with the platform being located between the root portion and the airfoil portion, the platform comprising:
an upstream side,
a downstream side,
side faces which extend from the upstream side to the downstream side,
an axial groove in each side face of the platform, said axial groove extends substantially perpendicular to the span direction with a minor component of extension in the span direction, and
a radial groove in each side face of the platform, said radial groove extends towards the axial groove with a component of extension in the span direction and a component of extension perpendicular to the span direction, and
wherein the radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove, and
wherein the second end is located at a distance from the axial groove so that a groove-free section is formed between the second end of the radial groove and the axial groove, and
wherein a further groove is present in each side face of the platform, wherein said further groove is open towards the axial groove and towards the upstream side of the platform and wherein said further groove is inclined away from the airfoil portion, as seen from the downstream side towards the upstream side, and
wherein the axial groove has an upstream end and a downstream end and wherein a junction of the further groove and the axial groove is separated by a length from the upstream end of the axial groove.

2. The gas turbine rotor blade as claimed in claim 1 ,
wherein the minor component of extension of the axial groove in the span direction is such that the axial groove is inclined towards the airfoil portion, as seen from the downstream side towards the upstream side.

3. The gas turbine rotor blade as claimed in claim 1 ,
wherein the component of extension of the radial groove perpendicular to the span direction is such that the radial groove is inclined towards the upstream side of the platform, as seen from the first end of the radial groove towards the second end of the radial groove.

4. The gas turbine rotor blade as claimed in claim 1 ,
wherein the first end of the radial groove is open.

5. The gas turbine rotor blade as claimed in claim 1 ,
wherein an extension of the groove-free section in the span direction between the second end of the radial groove and the axial groove is between 50% to 150% of a width of the axial groove.

6. The gas turbine rotor blade as claimed in claim 1 ,
wherein the minor component of extension of the axial groove in the span direction corresponds to between 3% to 10% of the an axial extension of the axial groove.

7. The gas turbine rotor blade as claimed in claim 1 ,
wherein the component of extension of the radial groove perpendicular to the span direction corresponds to between 30% to 50% of the component of extension of the radial groove in the span direction.

8. The gas turbine rotor blade as claimed in claim 1 ,
wherein the further groove is open at a distal end.

9. The gas turbine rotor blade as claimed in claim 1 ,
wherein the axial groove and the radial groove are arranged to overlap in an axial direction.

10. The gas turbine rotor blade as claimed in claim 1 ,
wherein the groove-free section has a dimension in the span direction between the axial groove and the radial groove.

11. The gas turbine rotor blade as claimed in claim 10 ,
wherein the dimension in the span direction provides a clear line-of-sight in an axial direction and into a cavity defined by the platform and wherein the cavity is supplied with compressed air.

12. A gas turbine rotor extending along an axial direction, comprising:
a number of gas turbine rotor blades according to claim 1 wherein the rotor blades are arranged side by side in a circumferential direction of the rotor in such a manner that gaps remain between the platforms of neighboring rotor blades,
axial seals which extend between neighboring rotor blades and which are held in place by the axial grooves in the side faces of the platforms of the neighboring rotor blades, and
radial seals which extend between neighboring rotor blades and which are held in place by the radial grooves in the side faces of the platforms of the neighboring rotor blades.

13. A method of assembling a rotor assembly, comprising:
firstly, mounting at least two rotor blades as claimed in claim 1 to a rotor disc,
secondly, inserting an axial seal strip through an open end of the further groove such that it is wholly or substantially within the axial groove, and
inserting a radial seal strip into the radial groove via the first end, wherein the first end is open.

14. The method as claimed in claim 13 , further comprising arranging a lock plate across the first end to prevent release of the radial seal strip.

15. The method as claimed in claim 13 , wherein a length of the axial seal strip is smaller than a length of the axial groove such that the inserting the axial seal strip comprises moving the axial seal strip through the further groove until the axial seal strip reaches the downstream end of the axial groove.

16. The method as claimed in claim 15 , wherein the inserting the axial seal strip further comprises moving an upstream end of the axial seal strip upwards so that the axial seal strip is fully located in the axial groove.

17. A gas turbine rotor blade including a root portion, a platform and an airfoil portion arranged along a span direction of the rotor blade with the platform being located between the root portion and the airfoil portion, the platform comprising:
an upstream side,
a downstream side,
side faces which extend from the upstream side to the downstream side,
an axial groove in each side face of the platform, said axial groove extends substantially perpendicular to the span direction with a minor component of extension in the span direction, and
a radial groove in each side face of the platform, said radial groove extends towards the axial groove with a component of extension in the span direction and a component of extension perpendicular to the span direction, and
wherein the radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove, and
wherein the second end is located at a distance from the axial groove so that a groove-free section is formed between the second end of the radial groove and the axial groove,
wherein a further groove is present in each side face of the platform, wherein said further groove is open towards the axial groove and towards the upstream side of the platform and wherein said further groove is inclined away from the airfoil portion, as seen from the downstream side towards the upstream side,
wherein the axial groove and the radial groove are arranged to overlap in an axial direction, and
wherein the overlap in the axial direction is at least a length defined from an upstream end of the axial groove to a junction of the further groove and the axial groove.

Assignees

• Siemens Ag

Inventors

• Bluck Richard
• Butler David
• Mugglestone Jonathan
• Overton David

Classifications

• F05D2250/294

  grooved · CPC title

• 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

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title