Method for cooling a turboengine rotor, and turboengine rotor

Patent metadata

Field	Value
Publication number	US-2016376891-A1
Application number	US-201615192510-A
Country	US
Kind code	A1
Filing date	Jun 24, 2016
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A method and device for cooling a turboengine rotor. A blade member includes a platform having a hot gas side and a coolant side. An airfoil is on the platform hot gas side and a blade foot section is on the platform coolant side. The blade foot section includes a blade shank and a blade root. The blade shank extends from the platform coolant side and is interposed between the blade root and the platform coolant side. The blade root includes root fixation features and is received by a fixation feature of a rotor shaft. A first fluid flows along the rotor front face and into a cavity of the blade shank and a second fluid flows within the blade shank cavity. The first fluid flow is relatively colder than the second fluid flow and a combined shank cavity fluid flow is formed inside the blade shank cavity.

First claim

1 . A method for cooling a turboengine rotor, the rotor including a rotor shaft and at least one blade member, the blade member including a platform, wherein the platform includes a hot gas side and a coolant side, an airfoil being provided on the platform hot gas side and a blade foot section being provided on the platform coolant side, wherein the blade foot section includes a blade shank and a blade root, wherein the blade shank extends from the platform coolant side and is interposed between the blade root and the platform coolant side, the blade root including root fixation features being provided on the blade root and being received by a fixation feature of the rotor shaft, wherein the rotor shaft fixation feature extends from a rotor front face and is provided on posts formed on the rotor shaft; an interconnection interface being formed between the fixation features being provided on the blade root and the rotor shaft, and extending to the rotor front face and forming an interface seam on the rotor front face; and a blade shank cavity being provided adjacent the platform coolant side, the method comprising:
guiding a first fluid flow along the rotor front face and into the blade shank cavity; a second fluid flow entering the blade shank cavity; choosing a source of the first fluid flow such that the first fluid flow is relatively colder than the second fluid flow; and admixing the second fluid flow with the first fluid flow inside the blade shank cavity to form a combined shank cavity fluid flow.

2 . The method according to claim 1 , wherein the first fluid flow is selectively guided over the interface seam present on the rotor front face before entering the blade shank cavity.

3 . The method according to claim 1 , comprising:
extracting the first fluid flow from a coolant plenum which is provided between a base of a groove provided between two adjacent rotor posts and the blade root.

4 . The method according to claim 1 , comprising:
guiding the second fluid flow along a front face of at least one of the blade root and the rotor shaft post from a location radially inwardly from the blade shank cavity and into the blade shank cavity.

5 . The method according to claim 1 , wherein the second fluid flow is a flow of pre-used coolant.

6 . The method according to claim 1 , wherein the second fluid flow originates from a cavity provided adjacent the rotor front face.

7 . The method according to claim 1 , wherein the first fluid flow and the second fluid flow enter the cavity separate from each other.

8 . A turboengine rotor, the rotor comprising:
a rotor shaft and at least one blade member, the blade member including a platform, wherein the platform includes a hot gas side and a coolant side, an airfoil being provided on the platform hot gas side and a blade foot section being provided on the platform coolant side, wherein the blade foot section includes a blade shank and a blade root, wherein the blade shank extends from the platform coolant side and is interposed between the blade root and the platform coolant side, the blade root including root fixation features being provided on the blade root and being received by a fixation feature of the rotor shaft, wherein the rotor shaft fixation feature extends from a rotor front face and is provided on posts formed on the rotor shaft; an interconnection interface being formed between the fixation features being provided on the blade root and the rotor shaft, and extending to the rotor front face and forming an interface seam on the rotor front face; and a blade shank cavity being provided adjacent the platform coolant side, wherein a first shank cavity supply duct is provided on the rotor front face and along the interface seam and is in fluid communication with the blade shank cavity.

9 . The turboengine rotor according to claim 8 , wherein a blade coolant supply plenum is provided between a base of a groove formed between two adjacent rotor shaft posts and the blade root and is in fluid communication with cooling ducts of the airfoil, wherein the first shank cavity supply duct is in fluid communication with the blade shank cavity at a downstream end and is in fluid communication with the blade coolant supply plenum at an upstream end, wherein a metering orifice is provided in a flow path between the blade coolant supply plenum and the first shank cavity supply duct.

10 . The turboengine rotor according claim 8 , wherein a second shank cavity supply duct is provided and is in fluid communication with the blade shank cavity at a downstream end, wherein said second shank cavity supply duct is provided along a front face of at least one of the blade root and the rotor shaft post, and an upstream end of the second shank cavity supply duct is provided radially inwardly from the downstream end.

11 . The turboengine rotor according to claim 8 , wherein a cover plate is provided covering at least a part of the front face, wherein the first and second shank cavity supply ducts are provided between the front face and the cover plate.

12 . The turboengine rotor according to claim 11 , wherein an upstream end of the second shank cavity supply duct is provided as an aperture in the cover plate.

13 . A cover plate for a turboengine rotor according to claim 11 , the cover plate comprising a first face and a second face and having a radial and a circumferential extent, the first face being configured and arranged to be mounted facing the rotor front face, wherein:
at least one flute is provided on the first face of the cover plate, said flute being arranged and configured to form a blade shank cavity supply duct when the cover plate is mounted on the rotor front face, the at least one flute extending from a radially inner position to a radially outer position.

14 . A cover plate for a turboengine rotor according to claim 11 , the cover plate comprising:
a first face and a second face and having a radial and a circumferential extent, the first face being configured and arranged to be mounted facing the rotor front face, wherein an aperture extends from the first to the second face, wherein the aperture is provided on a radially inner half of the cover plate and at least one flute is provided on the first face of the cover plate, said flute being arranged and configured to form a shank cavity supply duct when the cover plate is mounted on the rotor front face, wherein said at least one flute extends from the aperture to a position which is located on a larger radius than the aperture.

Assignees

• Ansaldo Energia Ip Uk Ltd

Inventors

• Bricaud Cyrille
• Simon-Delgado Carlos
• Zierer Thomas
• Steiger Ulrich Robert
• Strueken Stephan
• Didion Christoph

Classifications

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/3015

  with side plates · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title