System and method for domestic bleed circuit seals within a turbine

Patent metadata

Field	Value
Publication number	US-10316681-B2
Application number	US-201615168581-A
Country	US
Kind code	B2
Filing date	May 31, 2016
Priority date	May 31, 2016
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.

First claim

What is claimed is:

1. A turbine assembly comprising:
a rotor assembly comprising a shaft coupled to a plurality of rotor stages comprising a plurality of turbine blades, wherein said shaft and said plurality of turbine blades define a wheelspace therein; and
a plurality of seals in series, at least one seal of said plurality of seals coupled between a static support member and a respective rotor stage of said plurality of rotor stages such that a plurality of turbine cavities in series are defined within said wheelspace, wherein each turbine cavity of said plurality of turbine cavities defined by said plurality of seals receives a pressurized fluid flow that applies an axially aft force to said respective rotor stage of said plurality of rotor stages that at least partially reduces net rotor thrust generated by said rotor assembly during operation, said pressurized fluid flow further provides turbine purge within said wheelspace,
wherein at least one turbine cavity of said plurality of turbine cavities is defined between a first seal of said plurality of seals and a second seal of said plurality of seals such that the turbine cavity is between a first rotor stage and a second rotor stage of the plurality of rotor stages of the rotor assembly.

2. The turbine assembly in accordance with claim 1 , wherein each turbine cavity of said plurality of turbine cavities is defined between adjacent seals of said plurality of seals such that the turbine cavity is between adjacent rotor stages of said plurality of rotor stages.

3. The turbine assembly in accordance with claim 1 , wherein at least one seal of said plurality of seals extends between said static support member and a rotor.

4. The turbine assembly in accordance with claim 1 , wherein each turbine cavity of said plurality of turbine cavities is configured to be pressurized, wherein a pressure requirement of a first turbine cavity of said plurality of turbine cavities is substantially not equal to a pressure requirement of a second turbine cavity of said plurality of turbine cavities.

5. The turbine assembly in accordance with claim 1 , wherein each seal of said plurality of seals comprises a labyrinth seal.

6. The turbine assembly in accordance with claim 1 , wherein each seal of said plurality of seals comprises a non-contact seal.

7. A turbofan engine comprising:
an engine comprising a multistage compressor and a turbine, said turbine comprising a rotor assembly comprising a shaft coupled to a plurality of rotor stages comprising a plurality of turbine blades, wherein said shaft and said plurality of turbine blades define a wheelspace therein;
a fan powered by said turbine driven by gas generated in said engine; and
a bleed system comprising a plurality of seals in series, at least one seal of said plurality of seals coupled between a static support member and a respective rotor stage of said plurality of rotor stages such that a plurality of turbine cavities in series are defined within said wheelspace, wherein each turbine cavity of said plurality of turbine cavities defined by said plurality of seals to receives a pressurized fluid flow that applies an axially aft force to said respective rotor stage of said plurality of rotor stages that at least partially reduces net rotor thrust generated by said rotor assembly during operation, said pressurized fluid flow further provides turbine purge within said wheelspace,
wherein at least one turbine cavity of said plurality of turbine cavities is defined between a first seal of said plurality of seals and a second seal of said plurality of seals such that the turbine cavity is between a first rotor stage and a second rotor stage of the plurality of rotor stages of the rotor assembly.

8. The turbofan engine in accordance with claim 7 , wherein each turbine cavity of said plurality of turbine cavities is defined between adjacent seals of said plurality of seals such that the turbine cavity is between adjacent rotor stages of said plurality of rotor stages.

9. The turbofan engine in accordance with claim 7 , wherein at least one seal of said plurality of seals extends between said static support member and a rotor.

10. The turbofan engine in accordance with claim 7 , wherein each turbine cavity of said plurality of turbine cavities is configured to be pressurized, wherein a pressure requirement of a first turbine cavity of said plurality of turbine cavities is substantially not equal to a pressure requirement of a second turbine cavity of said plurality of turbine cavities.

11. The turbofan engine in accordance with claim 7 , wherein each seal of said plurality of seals comprises a labyrinth seal.

12. The turbofan engine in accordance with claim 7 , wherein each seal of said plurality of seals comprises a non-contact seal.

13. A method of assembling a turbine assembly comprising:
coupling a shaft to a plurality of rotor stages including a plurality of turbine blades forming a rotor assembly, wherein the shaft and the plurality of turbine blades define a wheelspace therein;
coupling a plurality of seals in series to the rotor assembly, at least one seal of the plurality of seals extends between a static support member and a respective rotor stage of the plurality of rotor stages such that a plurality of turbine cavities in series are formed within the wheelspace, wherein each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheelspace; and
forming at least one turbine cavity of the plurality of turbine cavities between a first seal of said plurality of seals and a second seal of said plurality of seals such that the turbine cavity is between a first rotor stage and a second rotor stage of the plurality of rotor stages of the rotor assembly.

14. The method of claim 13 further comprising forming each turbine cavity of the plurality of turbine cavities between adjacent seals of said plurality of seals such that the turbine cavity is between adjacent rotor stages of the plurality of rotor stages.

15. The method of claim 13 , wherein coupling the plurality of seals in series further comprises extending at least one seal of said plurality of seals between two static support members.

16. The method of claim 13 , wherein coupling a plurality of seals in series further comprises coupling a labyrinth seal.

17. The method of claim 13 , wherein coupling a plurality of seals in series further comprises coupling a non-contact seal.

Assignees

• Gen Electric

Inventors

• Narasimharao Jagata Laxmi
• Moniz Thomas Ory
• Thoppil Mohamed Musthafa
• Mondal Bhaskar Nanda
• Saha Atanu

Classifications

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F01D25/12

  Cooling · CPC title

• F01D3/00

  Machines or engines with axial-thrust balancing effected by working-fluid · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D11/04 Primary

  using sealing fluid, e.g. steam · CPC title