Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids

• US 9,797,259 B2
• Filed: 03/07/2014
• Issued: 10/24/2017
• Est. Priority Date: 03/07/2014
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Marsh, Jan H., Messmann, Stephen John, Scribner, Carmen Andrew
• Primary Examiner(s): Anderson, Gregory
• Assistant Examiner(s): Flores, Juan G
• Application Number:
  US14/200,168
• Publication Number:
  US 20150252688A1
• Time in Patent Office: 1,327 Days
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• 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 5/087 in the radial passages of the rotor disc
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F05D 2240/81 Cooled platforms

Abstract

A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system.

Claims

1. A turbine airfoil, comprising:

a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, a root at a first end of the airfoil and a tip at a second end opposite to the first end, and an airfoil cooling system positioned within interior aspects of the generally elongated hollow airfoil;

a snubber extending from the outer wall forming the generally elongated hollow airfoil toward an adjacent turbine airfoil positioned within a row of airfoils including the generally elongated hollow airfoil;

a snubber cooling system positioned within the snubber and extending to an under root slot, wherein the under root slot is positioned radially inward of the root of the generally elongated airfoil;

an ambient air cooling system in fluid communication with an ambient air source and in communication with the airfoil cooling system in the generally elongated hollow airfoil to provide ambient air to the airfoil cooling system;

a compressor bleed air cooling system in fluid communication with a compressor and with the snubber cooling system for providing compressor bleed air to the snubber cooling system; and

a compressor air manifold positioned radially inward of the root of the generally elongated airfoil,

wherein the compressor air manifold is positioned radially inward of the under root slot in a disc;

at least one movable air supply tube having an inlet in the compressor air manifold and an outlet movable between engagement with a channel within the generally elongated airfoil and nonengagement with the channel in which the outlet resides in the under root slot.

2. The turbine airfoil of claim 1, wherein the compressor in fluid communication with the compressor bleed air cooling system feeds compressor bleed air to a turbine of a gas turbine engine in which the turbine airfoil is mounted.

3. The turbine airfoil of claim 1, wherein the compressor in fluid communication with the compressor bleed air cooling system is a secondary compressor not in fluid communication with a turbine of a gas turbine engine in which the turbine airfoil is mounted.

4. The turbine airfoil of claim 1, wherein the at least one movable air supply tube further comprises a collar positioned adjacent the inlet adapted to mate with an inner wall forming the compressor air manifold to seal the at least one movable air supply tube to the compressor air manifold when the at least one movable air supply tube contains compressor air.

5. The turbine airfoil of claim 4, wherein the outlet of the at least one movable air supply tube further comprises a chamfered outer edge to facilitate the at least one movable air supply tube engaging the channel within the generally elongated airfoil.

6. A turbine airfoil, comprising:

a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, a root at a first end of the airfoil and a tip at a second end opposite to the first end, and an airfoil cooling system positioned within interior aspects of the generally elongated hollow airfoil;

a low pressure air cooling system in fluid communication with a low pressure air source and in communication with a low pressure subsystem of the airfoil cooling system in the generally elongated hollow airfoil to provide low pressure cooling air to the airfoil cooling system;

a high pressure cooling system in fluid communication with a high pressure air source and a high pressure subsystem of the airfoil cooling system for providing high pressure cooling air to the high pressure subsystem, wherein the high pressure cooling air has a higher pressure than the low pressure cooling air;

an under root slot positioned radially inward of the root of the generally elongated airfoil and a compressor air manifold positioned radially inward of the root of the generally elongated airfoil; and

at least one movable air supply tube having an inlet in the compressor air manifold and an outlet movable between engagement with a channel within the generally elongated airfoil and nonengagement with the channel in which the outlet resides in the under root slot.

7. The turbine airfoil of claim 6, wherein the low pressure air cooling system is an ambient air cooling system in fluid communication with an ambient air source and the low pressure subsystem is the airfoil cooling system in the generally elongated hollow airfoil that provides ambient air to the airfoil cooling system.

8. The turbine airfoil of claim 6, wherein the high pressure cooling system is a compressor bleed air cooling system in fluid communication with a compressor and the high pressure subsystem is a snubber cooling system for providing compressor bleed air to a snubber.

9. The turbine airfoil of claim 6, wherein the at least one movable air supply tube further comprises a collar positioned adjacent the inlet adapted to mate with an inner wall forming the compressor air manifold to seal the at least one movable air supply tube to the compressor air manifold when the at least one movable air supply tube contains compressor air.

10. The turbine airfoil of claim 9, wherein the outlet of the at least one movable air supply tube further comprises a chamfered outer edge to facilitate the at least one movable air supply tube engaging the channel within the generally elongated airfoil.