Turbine engine assembly and method of assembling the same

Patent metadata

Field	Value
Publication number	US-10280760-B2
Application number	US-201514870853-A
Country	US
Kind code	B2
Filing date	Sep 30, 2015
Priority date	Sep 30, 2015
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

First claim

What is claimed is:

1. A turbine assembly comprising:
a gas turbine engine comprising a rich burn combustor configured to combust an air-fuel mixture having excess fuel such that a flow of combusted gas having a depleted oxygen content is discharged therefrom and a lean burn combustor positioned downstream from said rich burn combustor, said lean burn combustor configured to combust the excess fuel in the flow of combusted gas such that the flow of exhaust gas discharged from said gas turbine engine has a depleted oxygen content, wherein at least one hot gas path component of each of the rich burn combustor and the lean burn combustor is formed at least partially from a ceramic matrix composite material; and
a treatment system positioned to receive the flow of exhaust gas from said gas turbine engine, said treatment system configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas directly into each of the rich burn combustor and the lean burn combustor towards said at least one hot gas path component of each of the rich burn combustor and the lean burn combustor,
wherein said at least one hot gas path component comprises a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over said at least one hot gas path component.

2. The turbine assembly in accordance with claim 1 , wherein said at least one hot gas path component comprises at least one of a combustor liner and a nozzle.

3. The turbine assembly in accordance with claim 1 , wherein said gas turbine engine further comprises a wheelspace and a rotor assembly comprising a rotor wheel positioned within said wheelspace, said treatment system further configured to channel the flow of treated exhaust gas towards said wheelspace to continuously purge fluid within said wheelspace.

4. The turbine assembly in accordance with claim 3 , wherein said rotor assembly comprises at least one second hot gas path component formed at least partially from a ceramic matrix composite material and the at least one second hot gas path component comprises at least one of a rotor blade and a shroud.

5. The turbine assembly in accordance with claim 1 , wherein said treatment system comprises a heat exchanger configured to cool the flow of exhaust gas such that a flow of water condensed from the flow of exhaust gas and a flow of cooled exhaust gas is discharged from said heat exchanger.

6. The turbine assembly in accordance with claim 5 , wherein said gas turbine engine comprises a compressor inlet configured to receive a portion of a flow of cooled exhaust gas from said heat exchanger.

7. The turbine assembly in accordance with claim 1 , wherein said treatment system comprises a carbon dioxide removal unit configured to remove carbon dioxide from the flow of exhaust gas.

8. A combined-cycle power generation system comprising:
a gas turbine engine comprising a rich burn combustor configured to corn bust an air-fuel mixture having excess fuel such that a flow of corn busted gas having a depleted oxygen content is discharged therefrom and a lean burn combustor positioned downstream from said rich burn combustor, said lean burn combustor configured to corn bust the excess fuel in the flow of corn busted gas such that the flow of exhaust gas discharged from said gas turbine engine has a depleted oxygen content, wherein at least one hot gas path component of each of the rich burn combustor and the lean burn combustor is formed at least partially from a ceramic matrix composite material; and
a heat recovery steam generator positioned to receive the flow of exhaust gas discharged from said gas turbine engine, said heat recovery steam generator configured to:
cool the flow of exhaust gas such that a flow of water condensed from the flow of exhaust gas and a flow of cooled exhaust gas is discharged from said heat recovery steam generator; and
channel the flow of cooled exhaust gas directly into each of the rich burn combustor and the lean burn combustor towards said at least one hot gas path component of each of the rich burn combustor and the lean burn combustor,
wherein said at least one hot gas path component comprises a plurality of cooling holes for channeling the flow of cooled exhaust gas therethrough, such that a protective film is formed over said at least one hot gas path component.

9. The system in accordance with claim 8 , further comprising a wheelspace and a rotor assembly comprising a rotor wheel positioned within said wheelspace, said heat recovery steam generator further configured to channel the flow of treated exhaust gas towards said wheelspace to continuously purge fluid within said wheelspace, wherein said rotor assembly comprises at least one second hot gas path component formed at least partially from a ceramic matrix composite material and the at least one second hot gas path component comprises at least one of a rotor blade and a shroud.

10. The system in accordance with claim 8 , wherein said at least one hot gas path component comprises at least one of a combustor liner and a nozzle.

11. The system in accordance with claim 8 , wherein said gas turbine engine comprises a compressor inlet configured to receive a portion of a flow of cooled exhaust gas from said heat recovery steam generator.

12. The system in accordance with claim 8 further comprising a carbon dioxide removal unit configured to remove carbon dioxide from the flow of cooled exhaust gas.

13. A method, comprising:
positioning a treatment system to receive a flow of exhaust gas from a gas turbine engine, the gas turbine engine including a rich burn combustor configured to combust an air-fuel mixture having excess fuel such that a flow of combusted gas having a depleted oxygen content is discharged therefrom and a lean burn combustor positioned downstream from said rich burn combustor, said lean burn combustor configured to combust the excess fuel in the flow of combusted gas such that the flow of exhaust gas discharged from said gas turbine engine has a depleted oxygen content, wherein at least one hot gas path component of each of the rich burn combustor and the lean burn combustor is formed at least partially from a ceramic matrix composite material and having a plurality of cooling holes defined therein, wherein the treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas; and
coupling the treatment system in flow communication with the at least one hot gas path component such that a protective film is formed over the at least one hot gas path component when the flow of treated exhaust gas is channeled directly into each of the rich burn combustor and the lean burn combustor towards the at least one hot gas path component of each of the rich burn combustor and the lean burn combustor.

14. The method in accordance with claim 13 , further comprising channeling the flow of treated exhaust gas towards a wheelspace and a rotor assembly comprising a rotor wheel positioned within said wheelspace to continuously purge fluid within said wheelspace, wherein said rotor assembly comprises at least one second hot gas path component formed at least partially from a ceramic matrix composite material and the at least one second hot gas path component comprises at least one of a rotor blade and a shroud.

15. The method in accordance with claim 13 , wherein positioning a treatment system comprises positioning a heat exchanger downstream from the gas turbine engine, the heat exchanger configured to cool the flow of exhaust

Assignees

• Gen Electric

Inventors

• Joshi Narendra Digamber
• Vandervort Christian Lee
• Luthra Krishan Lal
• Bunker Ronald Scott
• Haynes Joel Meier
• Tangirala Venkat Eswarlu

Classifications

• F23N2221/12

  Recycling exhaust gases · CPC title

• F23C9/08

  for reducing temperature in combustion chamber, e.g. for protecting walls of combustion chamber · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F02C6/003

  Gas-turbine plants with heaters between turbine stages · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title