Gas turbine

• US 5,695,319 A
• Filed: 04/04/1996
• Issued: 12/09/1997
• Est. Priority Date: 04/06/1995
• Status: Expired due to Term

• Current Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Hitachi, Ltd.
• Inventors: Higuchi, Shin'ichi, Matsumoto, Manabu, Noda, Masami, Kizuka, Nobuaki, Marushima, Shinya, Sekihara, Masaru, Kawaike, Kazuhiko, Ikeguchi, Takashi, Anzai, Shunichi
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/627,397
• Time in Patent Office: 614 Days
• Field of Search: 416/95, 416/96 R, 415/114, 415/115, 415/116, 60/39.75, 60/728
• US Class Current: 416/95
• CPC Class Codes: F01D 5/085 cooling fluid circulating inside the rotor
• CPC Class Codes: F05D 2260/2322 steam

Abstract

A vapor cooled gas turbine has a cooling system including a vapor supply port and a vapor recovery port, and the cooling system is formed so that vapor from the supply port is supplied to blades through a central supply passage in a rotor and the vapor having cooled the blades is recovered from the recovery port through a recovery passage spaced outwardly from the supply passage.

Claims

1. A gas turbine having a cooling system which cools the blades with vapor,

wherein said cooling system comprises a supply passage for supplying vapor to at least first and second stage blades and a vapor recovery passage for recovering the vapor supplied to said at least first and second stage blades, said vapor recovery passage including a first passage portion formed in a joining portion joining a disc and an adjacent disc of a rotor of said gas turbine and a cavity formed between first and second stage discs and fluidly connected to said first passage portion.

2. A gas turbine comprising a compressor and a gas turbine connected to said compressor through a distant piece, wherein said compressor has a compressor rotor having a cooling passage in which cooling steam flows, and said distant piece has a steam supply line in which steam flows into said cooling passage and a steam recovery line in which the steam having passed through said cooling passage flows.

3. A gas turbine in which the blades are cooled with vapor, wherein a vapor passage for recovering vapor having cooled said blades comprises a cavity between discs of a rotor of said gas turbine and a first passage portion formed in a spacer portion between said discs and fluidly connected to said cavity so as to flow the vapor from said blades towards an inner side of said rotor.

4. A gas turbine according to claim 3, wherein said spacer portion has a projecting portion for guiding vapor to be recovered into said vapor passage.

5. A gas turbine according to claim 4, further including a supply passage formed in a portion joining said discs for supplying vapor to the blades, wherein side surfaces of said discs are cooled with a part of the vapor in said supply passage.

6. A gas turbine constructed so as to cool the blades arranged in an outer peripheral portion of a rotor, using vapor,

wherein a supply passage for supplying vapor to said blades and a recovery passage for recovering vapor from said blades are provided inside said rotor, said supply passage being formed of a hole provided at a rotor axis and a cavity portion between members, and said recovery passage being formed of a hole formed axially in a cavity portion between members forming said rotor.

7. A gas turbine according to claim 6, wherein a heat resistor is provided on a wall surface of said recovery passage.

8. A gas turbine constructed so as to cool the blades arranged in an outer peripheral portion of a rotor, using vapor,

wherein a supply passage for supplying vapor to said blades and a recovery passage for recovering vapor from said blades are provided inside said rotor, said supply passage being formed of a hole provided in discs and a cavity portion between members, and said recovery passage being formed of a recovery hole formed in a disc joining portion.

9. A gas turbine which is constructed so as to be directly connected to a compressor and in which blades of the turbine are cooled with vapor, wherein

a cooling passage is formed inside a rotor of said compressor,

a supply passage for supplying vapor to said turbine blades is comprised of a hole provided at the axis of said compressor rotor, a cooling passage formed inside said compressor rotor, and a bore portion formed in a distant piece connecting said compressor rotor and a turbine rotor, and

a recovery passage is formed of a recovery hole provided in a disc joining portion.

10. A cooling apparatus for gas turbine blades, which cools the blades arranged in an outer peripheral portion of a rotor with vapor,

wherein a supply passage for supplying vapor to said blades and a recovery passage for recovering vapor from said blades are provided inside said rotor, said supply passage being formed of a hole provided at a rotor axis and a cavity portion between members forming said rotor, and said recovery passage being formed of a hole formed axially in a connecting portion connecting said members and a cavity portion between members forming said rotor.

11. A cooling apparatus for gas turbine blades, which cools the blades arranged in a disc outer peripheral portion of a rotor with vapor,

wherein a supply passage for supplying vapor to said blades and a recovery passage for recovering vapor from said blades are provided inside said rotor, said supply passage being formed of a central hole provided in said discs and a cavity portion between members, and said recovery passage including a recovery hole axially formed in a disc joining portion.

12. A cooling method for gas turbine blades, which cools the blades arranged in an outer peripheral portion of a rotor with vapor, wherein

vapor supply to and vapor recovery from said blades are effected through flow passages, the vapor supply is effected from a rotor axis side and the vapor recovery is effected in a more outer side than a position of the vapor supply, the vapor cooling said blades being recovered outside the rotor.

13. A gas turbine having a cooling system which cools the blades with vapor,

wherein said cooling system comprises a supply system for supplying vapor to said blades and a recovery system for recovering vapor from said blades, said supply system including a supply passage, and said recovery system including a recovery passage spaced outwardly from said supply passage, the vapor being recovered from a turbine rotor through said vapor recovery system.

14. A gas turbine having a cooling system which cools the blades with vapor,

wherein said cooling system comprises a supply port formed at a rotor axial end of said gas turbine for supplying vapor and a recovery port formed at a rotor axial end of said gas turbine for recovering vapor from said blades out of said rotor, said supply port being positioned at a position closer to the rotor axis than said recovery port, and said supply port is fluidly communicated with said recovery port through a vapor passage in which said blades to be cooled are disposed.