Arrangement of cooling channels in a turbine blade

Patent metadata

Field	Value
Publication number	US-2016208622-A1
Application number	US-201415023392-A
Country	US
Kind code	A1
Filing date	Sep 17, 2014
Priority date	Sep 25, 2013
Publication date	Jul 21, 2016
Grant date	—

Abstract

An arrangement of a plurality of cooling channels within a turbine blade conveys cooling fluid, wherein the cooling channels lead through the turbine blade, which has a blade root, a blade tip, a leading edge, and a trailing edge, to one or more cooling-fluid outlets, wherein the cooling channels are connected to each other at selected locations and extend separately from each other in other regions in such a way that, in the event of damage to the turbine blade in the region of one cooling channel, the cooling by the other cooling channels remains largely unimpaired, wherein at least one cooling channel begins in a region near the leading edge and near the blade root and leads as a diagonal channel through the turbine blade into a region near the trailing edge and near the blade tip.

First claim

1 .- 10 . (canceled)

11 . An arrangement for conveying cooling fluid, comprising:
multiple cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) within a turbine blade, wherein the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) lead through the turbine blade, which has a blade root, a blade airfoil tip, a leading edge and a trailing edge, to one or more cooling fluid outlets, wherein the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) are connected to one another at specific points and run separate from one another in other regions such that, in the event of damage to the turbine blade in the region of one cooling channel ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ), the cooling through the other cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) remains largely unimpaired, wherein at least one cooling channel begins in a region close to the leading edge and close to the blade root and runs as a diagonal channel ( 9 ) through the turbine blade into a region close to the trailing edge and close to the blade airfoil tip, wherein two cooling channels ( 6 , 7 ) begin at the blade root, in a region close to the leading edge, and end in a region close to the blade root, and are connected to one another and to the diagonal channel ( 9 ), and wherein other cooling channels ( 11 , 13 , 14 ) branch off from the diagonal channel ( 9 ) in the direction of the trailing edge and cooling channels ( 15 , 16 ) branch off in the direction of the blade airfoil tip, and wherein the cooling channels ( 11 , 13 , 14 ) branching off in the direction of the trailing edge run essentially perpendicular to the trailing edge and/or the cooling channels ( 15 , 16 ) running in the direction of the blade airfoil tip run essentially parallel to the trailing edge.

12 . The arrangement as claimed in claim 11 ,
wherein the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) are connected to one another such that, when the arrangement is flowed through, cooling fluid flows regularly from one of the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) into another of the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ).

13 . The arrangement as claimed in claim 11 ,
wherein the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) are separated from an internal wall of the turbine blade by means of a perforated plate or a device in the manner of a perforated plate, such that the cooling fluid can arrive at the internal wall of the turbine blade essentially perpendicular to the latter.

14 . The arrangement as claimed in claim 11 ,
wherein at least one of the cooling channels ( 6 , 7 , 9 , 11 , 12 , 13 , 14 , 15 , 16 , 17 ) begins at the blade root, in a region close to the leading edge.

15 . The arrangement as claimed in claim 14 ,
wherein a cooling channel, into which open the cooling channels ( 15 , 16 ) running in the direction of the blade airfoil tip, runs parallel to the blade airfoil tip.

16 . The arrangement as claimed in claim 11 ,
wherein cooling fluid outlets, at which cooling fluid can pass from the region within the turbine blade into a region outside the turbine blade, are present in the region of the trailing edge.

17 . The arrangement as claimed in claim 11 ,
wherein at least one cooling fluid outlet is present at the blade root, in the region of the trailing edge.

Assignees

• Siemens Ag

Inventors

• Ahmad Fathi
• Burzych Thomas
• Hummel Eugen
• Kunze Gordon Emanuel
• Preuten Frank
• Schneider Thomas Alexis
• Teuber Hannes

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/188

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