Controlling cooling flow in a cooled turbine vane or blade using an impingement tube

Patent metadata

Field	Value
Publication number	US-10502071-B2
Application number	US-201515302071-A
Country	US
Kind code	B2
Filing date	Mar 10, 2015
Priority date	Apr 16, 2014
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.

First claim

The invention claimed is:

1. An airfoil for a gas turbine, the airfoil comprising:
an outer shell comprising an inner volume,
an inner shell arranged within the inner volume of the outer shell,
wherein the inner shell comprises an inner nose section and an inner tail section,
wherein a high pressure side of the inner shell is formed along a first surface section between the inner nose section and the inner tail section,
wherein a low pressure side of the inner shell is formed along a second surface section which is located opposite to the first surface section between the inner nose section and the inner tail section,
wherein the inner shell is spaced apart from the outer shell such that
a first cooling channel is formed along the high pressure side between the inner nose section and the inner tail section, and
a second cooling channel is formed along the low pressure side between the inner nose section and the inner tail section,
wherein the first cooling channel and the second cooling channel merge into a common cooling channel at the inner tail section,

a first tail fin arranged between the first cooling channel and the common cooling channel and defining a first fluid passage configured to control a first mass flow rate of a cooling fluid flowing through the first cooling channel, and a second tail fin arranged between the second cooling channel and the common cooling channel and defining a second fluid passage configured to control a second mass flow rate of a cooling fluid flowing through the second cooling channel,
wherein the first fluid passage and the second fluid passage comprise different flow areas,
wherein the first tail fin is configured to deform in response to a pressure increase, thereby increasing a flow area of the first fluid passage, and
wherein the second tail fin is configured to deform in response to the pressure increase, thereby increasing a flow area of the second fluid passage.

2. The airfoil according to claim 1 ,
wherein the first tail fin comprises at least one first through hole for forming the first fluid passage, and wherein the second tail fin comprises at least one second through hole for forming the second fluid passage.

3. The airfoil according to claim 2 ,
wherein a first size of the at least one first through hole differs to a second size of the at least one second through hole.

4. The airfoil according to claim 1 ,
wherein the high pressure side and the low pressure side are connected within the inner tail section and form an inner tail edge extending along a span width of the inner shell.

5. The airfoil according to claim 1 ,
wherein the first tail fin is secured to the inner tail section and extends as a cantilever toward the high pressure side of the outer shell, wherein the second tail fin is secured to the inner tail section and extends as a cantilever toward the low pressure side of the outer shell, wherein the first fluid passage comprises a first gap formed between a free end of the first tail fin and the high pressure side of the outer shell, and wherein the second fluid passage comprises a second gap formed between a free end of the second tail fin and the low pressure side of the outer shell.

6. The airfoil according to claim 5 ,
wherein the first tail fin is elastically deformable such that the first gap increases with increasing pressure inside the first cooling channel.

7. The airfoil according to claim 6 , further comprising
a first retaining element arranged within the common cooling channel downstream of the first tail fin, wherein upon reaching a maximum predetermined deformation of the first tail fin the free end of the first tail fin abuts the first retaining element such that further deformation of the first tail fin and associated increase in the first gap is prevented.

8. The airfoil according to claim 5 ,
wherein the second tail fin is elastically deformable such that the second gap increases with increasing pressure inside the second cooling channel.

9. The airfoil according to claim 1 ,
wherein the outer shell comprises an outer nose section,
wherein the inner shell is arranged within the inner volume such that the inner nose section and the outer nose section are spaced apart from each other such that a nose volume is generated which is connected to the first cooling channel and the second cooling channel, wherein the inner nose section comprises a fluid outlet such that a cooling fluid is ejectable from the inside of the inner shell into the nose volume.

10. The airfoil according to claim 1 ,
wherein the high pressure side and/or the low pressure side are free of further fluid outlets.

11. A gas turbine, comprising
an airfoil according to claim 1 wherein the airfoil forms a stationary vane or a rotatable blade of the gas turbine.

12. The airfoil according to claim 1 , wherein the first fluid passage comprises a first flow area, the second fluid passage comprises a second flow area, and the first flow area is less than the second flow area.

13. The airfoil according to claim 8 , further comprising:
a second retaining element arranged within the common cooling channel downstream of the second tail fin, wherein upon reaching a maximum predetermined deformation of the second tail fin the free end of the second tail fin abuts the second retaining element such that further deformation of the second tail fin and associated increase in the second gap is prevented.

14. The airfoil according to claim 1 , wherein the first tail fin extends as a cantilever across the first cooling channel, wherein the second tail fin extends as a cantilever across the second cooling channel, wherein the first fluid passage comprises a first gap bounded by a free end of the first tail fin, and wherein the second fluid passage comprises a second gap bounded by a free end of the second tail fin.

15. The airfoil according to claim 14 , wherein the first tail fin is elastically deformable such that the first gap increases with increasing pressure inside the first cooling channel, and wherein the second tail fin is elastically deformable such that the second gap increases with increasing pressure inside the second cooling channel.

16. A method of manufacturing an airfoil for a gas turbine, the method comprising
providing an outer shell comprising an inner volume,
arranging an inner shell within the inner volume of the outer shell,
wherein the inner shell comprises an inner nose section and an inner tail section,
wherein a high pressure side of the inner shell is formed along a first surface section between the inner nose section and the inner tail section,
wherein a low pressure side of the inner shell is formed along a second surface section which is located opposite to the first surface section between the inner nose section and the inner tail section,
wherein the inner shell is spaced apart from the outer shell such that
a first cooling channel is formed along the high pressure side between the inner nose section and the inner tail section, and
a second cooling channel is formed along the low pressure side between the inner nose section and the inner tail section,
wherein the first cooling channel and the second cooling channel merge into a common cooling channel at the inner tail section,

arranging a first tail fin between the first cooling channel and the common cooling channel and defining a first fluid passage configured to control a first mass flow rate of a cooling fluid flowing through the first cooling channel, and arranging a second tail fin between the second cooling channel and the common cooling

Assignees

• Siemens Ag

Inventors

• Davis Anthony
• Mugglestone Jonathan

Classifications

• F01D5/189 Primary

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

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2220/32

  in gas turbines · CPC title