Blade for a gas turbine, method for manufacturing a turbine blade, and gas turbine with a blade

• US 9,188,011 B2
• Filed: 11/29/2011
• Issued: 11/17/2015
• Est. Priority Date: 11/29/2010
• Status: Expired due to Fees

• Current Assignee: General Electric Technology GmbH (GE Aerospace)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Khanin, Alexander Anatolievich
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Lee, Jr., Woody A
• Application Number:
  US13/306,050
• Publication Number:
  US 20120134845A1
• Time in Patent Office: 1,449 Days
• Field of Search: 415/115, 416/95, 416/96.A, 416/96.R, 416/97.R
• US Class Current: 1/1
• CPC Class Codes: F01D 5/081 Cooling fluid being directed on the side of the rotor disc or at the roots of the blades F01D5/087 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: Y10T 29/49343 Passage contains tubular insert

Abstract

A blade (30′) for a gas turbine has an airfoil (31) and a blade root (32) for mounting the blade (30) on a rotor shaft of the gas turbine. The airfoil (31) is provided with cooling channels (33, 35) in the interior thereof, which cooling channels (33, 35) preferably extend along the longitudinal direction and can be supplied with cooling air (45) through cooling air supply passages (40-43) within the blade root (32). The blade root (32) includes a blade channel (40) running transversely through the blade root (32) and is connected to the cooling channels (33, 35), and an insert (41) is inserted into the blade channel (40) for determining the final configuration and characteristics of the connections between the blade channel (40) and the cooling channels (33, 35).

Claims

1. A blade for a gas turbine having a rotor shaft, the blade comprising:

an airfoil extending along a longitudinal direction, and a blade root configured and arranged to mount said blade on the rotor shaft, wherein said blade root includes a cooling air supply arranged within said blade root and said airfoil comprises interior cooling channels, which cooling channels extend along the longitudinal direction and can be supplied with cooling air through the blade root cooling air supply;

wherein said blade root comprises a blade channel running transversely through said blade root and being connected to said cooling channels, and an insert positioned in said blade channel and including fluid connections between said blade channel and said cooling channels;

wherein the blade channel comprises a cylindrical channel, and the insert is of a tubular configuration such that the insert fits exactly into said cylindrical channel;

wherein the insert comprises a wall and at least one nozzle in said wall, through which at least one nozzle of said cooling channels is connected to said blade channel, and which at least one nozzle determines a mass flow of cooling air entering said one cooling channel;

wherein said insert is configured and arranged for cooling air to be supplied to said insert at one end of said insert; and

wherein said insert is configured and arranged for cooling air to exit said insert at an opposite end of said insert.

2. A blade according to claim 1, comprising:

a wall separating two adjacent cooling channels, said two adjacent cooling channels being fluidly connected via said blade channel, and said insert is configured and arranged to close said connection between said adjacent cooling channels.

3. A blade according to claim 1, wherein said insert is brazed to said blade.

4. A blade according to claim 1, wherein said insert includes a nozzle at said opposite end of said insert through which said cooling air can exit.

5. A blade for a gas turbine having a rotor shaft, the blade comprising:

an airfoil extending along a longitudinal direction, and a blade root configured and arranged to mount said blade on the rotor shaft, wherein said blade root includes a cooling air supply arranged within said blade root and said airfoil comprises interior cooling channels, which cooling channels extend along the longitudinal direction and can be supplied with cooling air through the blade root cooling air supply;

wherein said blade root comprises a blade channel running transversely through said blade root and being connected to said cooling channels, and an insert positioned in said blade channel and including fluid connections between said blade channel and said cooling channels;

wherein the blade channel comprises a cylindrical channel, and the insert is of a tubular configuration such that the insert fits exactly into said cylindrical channel;

wherein the insert comprises a wall and at least one nozzle in said wall, through which at least one nozzle of said cooling channels is connected to said blade channel, and which at least one nozzle determines a mass flow of cooling air entering said one cooling channel; and

wherein said insert is configured and arranged for cooling air to exit said insert at an opposite end of said insert.

6. A blade according to claim 5, wherein said insert includes a nozzle at said opposite end of said insert through which said cooling air can exit.

7. A blade according to claim 5, comprising:

a wall separating two adjacent cooling channels, said two adjacent cooling channels being fluidly connected via said blade channel, and said insert is configured and arranged to close said connection between said adjacent cooling channels.

8. A blade according to claim 5, wherein said insert is brazed to said blade.

9. A gas turbine comprising:

a rotor with a shaft and plurality of blades mounted to the rotor shaft, the rotor shaft including a cooling air supply configured and arranged to supply cooling air through said rotor shaft to said blades; and

wherein said blades comprise an airfoil extending along a longitudinal direction, and a blade root configured and arranged to mount said blade on the rotor shaft, wherein said blade root includes a cooling air supply arranged within said blade root and said airfoil comprises interior cooling channels, which cooling channels extend along the longitudinal direction and can be supplied with cooling air through the blade root cooling air supply;

wherein said blade root comprises a blade channel running transversely through said blade root and being connected to said cooling channels, and an insert positioned in said blade channel and including fluid connections between said blade channel and said cooling channels;

wherein the blade channel comprises a cylindrical channel, and the insert is of a tubular configuration such that the insert fits exactly into said cylindrical channel;

wherein the insert comprises a wall and at least one nozzle in said wall, through which at least one nozzle of said cooling channels is connected to said blade channel, and which at least one nozzle determines a mass flow of cooling air entering said one cooling channel;

wherein said insert is configured and arranged for cooling air to be supplied to said insert at one end of said insert; and

wherein said insert is configured and arranged for cooling air to exit said insert at an opposite end of said insert.