Turbine have a first and second rotor disc and a first and second cooling fluid conduit wherein the second cooling fluid conduit is extended through an annular axially extended bore having a radially outer extent defined by a radially innermost surface of the rotor discs

Patent metadata

Field	Value
Publication number	US-11143041-B2
Application number	US-201715401461-A
Country	US
Kind code	B2
Filing date	Jan 9, 2017
Priority date	Jan 9, 2017
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

The turbine includes a first turbine rotor disc, a second turbine rotor disc, a first source of cooling fluid, and a first cooling fluid conduit. The first turbine rotor disc has a first outer circumference and a first plurality of blades spaced along the first outer circumference. The second turbine rotor disc has a second outer circumference and a second plurality of blades spaced along the second outer circumference. The first cooling fluid conduit is configured to channel a first flow of cooling fluid from the first source of cooling fluid through the first turbine rotor disc to a blade of the second plurality of blades.

First claim

What is claimed is:

1. A turbine comprising:
a first turbine rotor disc having a first outer circumference and a first plurality of blades spaced along the first outer circumference;
a second turbine rotor disc having a second outer circumference and a second plurality of blades spaced along the second outer circumference;
a first source of cooling fluid;
a first cooling fluid conduit configured to channel a first flow of cooling fluid in serial flow from said first source of cooling fluid to a first forward portion of the first turbine rotor disc, to the first outer circumference of the first turbine rotor disc, to a second forward portion of the second turbine rotor disc, and to the second outer circumference of the second turbine rotor disc; and
a second cooling fluid conduit extended through an annular axially extended bore having a radially outer extent defined by a radially innermost surface of said first turbine rotor disc and second turbine rotor disc, wherein the second cooling fluid conduit is configured to channel a second flow of cooling fluid through said annular axially extended bore.

2. The turbine of claim 1 , wherein said first cooling fluid conduit extends in serial flow communication from said first source of cooling fluid to the first forward portion of the first turbine rotor disc, to the first outer circumference of the first turbine rotor disc, to a first aft portion of the first turbine rotor disc, and further wherein the first cooling fluid conduit extends through one or more of said first plurality of blades.

3. The turbine of claim 1 , wherein said first cooling fluid conduit extends in serial flow communication to the first forward portion of the first turbine rotor disc, to a first aft portion of the first turbine rotor disc, to the second forward portion at said second turbine rotor disc, and then to the second outer circumference of the second turbine rotor disc.

4. The turbine of claim 1 , wherein the second cooling fluid conduit is configured to channel the second flow of cooling fluid inward along the radial direction of a bore of each respective first turbine rotor disc and second turbine rotor disc.

5. The turbine of claim 1 , further comprising a second source of cooling fluid coupled in flow communication with said second cooling fluid conduit, and wherein the second cooling fluid conduit is fluidly separate from the first cooling fluid conduit.

6. The turbine of claim 5 , wherein said second source of cooling fluid comprises a bearing sump comprising a sump conduit configured to channel the second cooling fluid to the second cooling fluid conduit.

7. The turbine of claim 6 , further comprising a hot gas flow path through said turbine and configured to channel a flow of hot gas, said second cooling fluid conduit configured to channel said second flow of cooling fluid to said hot gas flow path.

8. The turbine of claim 1 , wherein said first source of cooling fluid comprises a compressor.

9. A core engine comprising an axis of rotation and configured to generate a flow of high energy combustion gases, said core engine comprising:
a compressor, a combustor, and a turbine coupled in serial flow communication, said compressor coupled to said turbine by a shaft, said turbine comprising:
a rotor comprising at least one disc, said at least one disc including opposing axially facing surfaces and a circumferentially extending radially facing surface extending between the axially facing surfaces;
a plurality of blades positioned on said radially facing surface of said at least one disc;
a first source of cooling fluid;
a first cooling fluid conduit configured to channel a first flow of cooling fluid in serial flow from said first source of cooling fluid to a first forward axially facing surface, to a radially facing surface, and then to a first aft axially facing surface, and wherein the first cooling fluid is then configured to channel the first flow of cooling fluid to one or more of said plurality of blades positioned on said at least one disc; and

a second cooling fluid conduit extended through an annular axially extended bore having a radially outer extent defined by a radially innermost surface of said first turbine rotor disc and second turbine rotor disc, wherein the second cooling fluid conduit is configured to channel a second flow of cooling fluid.

10. The core engine of claim 9 , wherein said at least one disc comprises a first turbine rotor disc and a second turbine rotor disc coupled to said first turbine rotor disc, wherein said first cooling fluid conduit is configured to channel the first flow of cooling fluid from said first source of cooling fluid to the first forward axially facing surface of the first turbine rotor disc, to the radially facing surface of the first turbine rotor disc, and then to the first aft axially facing surface of the first turbine rotor disc, and then to one or more of said plurality of blades positioned on said radially facing surface of said second turbine rotor disc.

11. The core engine of claim 10 , wherein said first cooling fluid conduit extends through one or more of said plurality of blades positioned on said radially facing surface of said first turbine rotor disc.

12. The core engine of claim 10 , wherein said first cooling fluid conduit extends through a second forward axially facing surface of said second turbine rotor disc.

13. The core engine of claim 9 , wherein the second cooling fluid conduit is configured to channel the second flow of cooling fluid inward along a radial direction of a bore of each respective first turbine rotor disc and second turbine rotor disc.

14. The core engine of claim 13 , further comprising a second source of cooling fluid coupled in flow communication with said second cooling fluid conduit.

15. The core engine of claim 14 , wherein said second source of cooling fluid comprises a bearing sump, said bearing sump comprising a sump conduit configured to channel the second cooling fluid to the second cooling fluid conduit.

16. The core engine of claim 15 , further comprising a hot gas flow path through said turbine, said second cooling fluid conduit configured to channel said second flow of cooling fluid to said hot gas flow path, and wherein the first cooling fluid conduit and the second cooling fluid conduit are fluidly separate from one another before the hot gas flow path.

17. A method of cooling a turbine, the turbine comprising a first turbine rotor disc and a second turbine rotor disc, the first turbine disc having a first outer circumference and a first plurality of blades spaced along the first outer circumference, the second turbine rotor disc having a second outer circumference and a second plurality of blades spaced along the second outer circumference, said method comprising:
channeling a first flow of cooling fluid through a first cooling fluid conduit in serial flow to a first forward portion of the first turbine disc, to the first outer circumference of the first turbine disc, and to a second forward portion of the second turbine disc, and to the second outer circumference of the second turbine disc, and to a blade of the second plurality of blades; and
channeling a second flow of cooling fluid through a second coding fluid conduit, extended through an annular axially extended bore having a radially outer extent defined by a radially innermost surface of the first turbine rotor disc and the second turbine rotor disc, to a hot gas flow path within the turbine.

18. The method of claim 17 , further comprising channeling the first flow of

Assignees

• Gen Electric

Inventors

• Johnson Brian David
• Waslo Daniel

Classifications

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D5/3015 Primary

  with side plates · 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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title