Bore basket for a gas powered turbine

Patent metadata

Field	Value
Publication number	US-10280792-B2
Application number	US-201514627030-A
Country	US
Kind code	B2
Filing date	Feb 20, 2015
Priority date	Feb 21, 2014
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

Gas turbine engines include bore baskets to facilitate rotor bore cooling. One such bore basket for utilization in a gas turbine engine includes two cylinders that guide a cooling flow through a bore opening. The cylinders define an axially aligned gap that further directs fluid flow when a cooling fluid is injected into the system.

First claim

The invention claimed is:

1. A gas turbine comprising:
a compressor section;
a combustor fluidly connected to the compressor;
a turbine section fluidly connected to the combustor;
a rotor bore opening disposed radially inward of a plurality of rotors in one of said compressor section and said turbine section, wherein the rotor bore opening is defined by a forward hub structure, a bore basket and a connection between said bore basket and an aft most rotor bore in said rotor bore opening;
said bore basket defines a cylinder having an axis, and wherein said bore basket comprises;
a radially outward first cylinder having at least one radially aligned opening on a first end of said bore basket;
a radially inward second cylinder having a radially aligned opening on a second end of said bore basket opposite said first end, and being disposed within said radially outward first cylinder;
an axially aligned gap defined by said radially outward first cylinder and said radially inward second cylinder; and

a first cooling fluid flowpath defined between said first cylinder and said second cylinder;
a second cooling flowpath defined radially inward of the second cylinder; and
wherein the first cooling flowpath and the second cooling flowpath merge at the radially aligned opening on the second end of the bore basket.

2. The gas turbine of claim 1 , wherein said first end of said bore basket is aftward relative to fluid flow, and wherein said second end of said bore basket is forward relative to fluid flow.

3. A gas turbine comprising:
a compressor section;
a combustor fluidly connected to the compressor;
a turbine section fluidly connected to the combustor;
a rotor bore opening disposed radially inward of a plurality of rotors in one of said compressor section and said turbine section, wherein the rotor bore opening is defined by a forward hub structure, a bore basket and a connection between said bore basket and an aft most rotor bore in said rotor bore opening;
said bore basket defines a cylinder having an axis, and wherein said bore basket comprises;
a radially outward first cylinder having at least one radially aligned opening on a first end of said bore basket;
a radially inward second cylinder having a radially aligned opening on a second end of said bore basket opposite said first end, and being disposed within said radially outward first cylinder;
an axially aligned gap defined by said radially outward first cylinder and said radially inward second cylinder;
wherein said radially outward first cylinder contacts said radially inward second cylinder at a radial protrusion on said second end of said bore basket, and contacts said radially inward second cylinder at a retaining structure on said first end of said bore basket; and
wherein one of said radially outward first cylinder and said radially inward second cylinder comprises a snap fit arm and said snap fit arm is disposed on said first end of said bore basket.

4. The gas turbine of claim 3 , wherein
said retaining structure is a retaining ring positioned aft of a pair of contact surfaces;
said radially outward first cylinder contacts said radially inward second cylinder;
said retaining ring is disposed at least partially within one of said radially outward first cylinder and said radially inward second cylinder; and
said retaining ring contacts a radially aligned edge of the other of said radially outward first cylinder and said radially inward second cylinder.

5. The gas turbine of claim 3 , wherein said retaining structure is a radially protruding shoulder disposed on said radially inward second cylinder, and wherein said radially outward first cylinder contacts at least two surfaces of said shoulder.

6. The gas turbine of claim 5 , wherein a forward end of said first radially outward cylinder contacts a structure of said gas turbine.

7. The gas turbine of claim 3 , wherein said snap fit arm comprises a radially aligned snap fit feature on an axial end of said snap fit arm.

8. The gas turbine of claim 1 , further comprising a hub structure at least partially defining a forward wall of said rotor bore opening, and wherein said structure includes a cool air inlet into said rotor bore opening, and wherein said hub, said rotor bore opening, and said bore basket define a cool air flowpath from said inlet, along a radially outward surface of said first radially outward cylinder, through said radially aligned opening on a first end of said bore basket into said gap defined by said radially outward first cylinder and said radially inward second cylinder, and through said radially aligned opening on a second end of said bore basket opposite said first end.

9. The gas turbine of claim 1 , wherein said radially outward first cylinder and said radially inward second cylinder are maintained in position relative to each other at least in part via a tight fit connection between at least one contact surface of the radially inward cylinder and at least one contact surface of the radially outward cylinder.

10. The gas turbine of claim 1 , wherein said radially outward first cylinder and said radially inward second cylinder are maintained in position relative to each other at least in part via compression forces of gas turbine engine components external to said bore basket.

11. The gas turbine of claim 1 , further comprising a mechanical interconnection connecting said radially outward first cylinder to said radially inward second cylinder, such that said radially outward first cylinder and said radially inward second cylinder are a unitary structure.

12. The gas turbine of claim 11 , wherein said mechanical interconnection is at least one of a brazed connection and a welded connection.

13. The gas turbine of claim 11 , wherein the bore basket further comprises a plurality of structural struts connecting said first radially outward cylinder to said radially inward cylinder, and wherein the plurality of structural struts are disposed circumferentially about said radially inward strut at least one axial position.

14. The gas turbine of claim 13 , wherein said plurality of structural struts are mechanically interconnected with at least one of said first radially outward cylinder and said radially inward cylinder, such that plurality of structural struts and the bore basket comprise a unitary structure.

15. The gas turbine of claim 11 ,
wherein said radially inward cylinder comprises a seat structure having an axially aligned surface, wherein said axially aligned surface of said seat structure contacts an inner surface of said first radially outward cylinder; and
wherein said mechanical interconnection is a mechanical interconnection between said axially aligned surface of said seat structure and said inner surface of said first radially outward cylinder.

16. The gas turbine engine of claim 1 , wherein the second cooling flowpath is isolated from the first cooling flowpath by said radially inward second cylinder.

17. The gas turbine engine of claim 1 , wherein the first cooling flowpath originates at a forward end of the bore basket, and wherein the second cooling flowpath originates at an aft end of the bore basket.

18. The gas turbine engine of claim 17 , wherein the first cooling flowpath travels axially aft along a radially outer surface of the first radially outward cylinder, through the first opening at the first end of said bore basket, and axially forward through said gap.

19. A bore basket arrangement comprising:
bore basket defining a cylinder having an axis, and wherein sa

Assignees

• United Technologies Corp

Inventors

• Gons William M

Classifications

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · 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

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D25/12 Primary

  Cooling · CPC title

• F05D2240/20

  Rotors · CPC title