Combustor of gas turbine with features for vibration reduction and increased cooling

• US 4,297,843 A
• Filed: 10/12/1979
• Issued: 11/03/1981
• Est. Priority Date: 10/16/1978
• Status: Expired due to Term

• Current Assignee: Hitachi, Ltd.
• Original Assignee: Hitachi, Ltd.
• Inventors: Sato, Isao, Uchiyama, Yoshihiro, Iizuka, Nobuyuki, Kato, Fumio, Hata, Tsuneyuki
• Primary Examiner(s): Garrett, Robert E.
• Application Number:
  US06/084,438
• Time in Patent Office: 753 Days
• Field of Search: 60/39.37, 60/752, 60/39.32
• US Class Current: 60/796
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2240/126 Baffles or ribs
• CPC Class Codes: F23R 3/02 characterised by the air-flow or gas-flow configuration reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58
• CPC Class Codes: F23R 3/46 Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Abstract

A combustor of a gas turbine having a plurality of liners defining combustion chambers, and transition pieces adapted to rectify the flow of the combustion gas discharged from the liners before the combustion gas is introduced to the turbine. A guide plate is disposed in the gap between each pair of adjacent transition pieces near the gas outlets of the latter so as to guide the flow of air to the radially outer surfaces of adjacent transition pieces, thereby to improve the cooling of these surfaces and, at the same time, to mechanically connect the adjacent transition pieces to suppress the vibration of the transition pieces.

Claims

1. A combustor of a gas turbine having a plurality of combustor liners, a plurality of transition pieces connected to respective liners and adapted to rectify the flow of combustion gas coming from said liners, and a plurality of outer casings surrounding respective combinations of said liners and said transition pieces, comprising a guide plate having a radial portion disposed in each gap formed between each pair of adjacent transition pieces, said guide plate being adapted to rectify the air flowing through said gap, each guide plate having circumferential members that overlie the transition pieces and are attached to the radial portion of the guide plate, and said circumferential members form a gap between the adjacent circumferential members for exit of the cooling air.

2. A combustor of a gas turbine as claimed in claim 1, wherein each of said guide plates is disposed in the vicinity of the gas outlet of each transition piece.

3. A combustor of a gas turbine as claimed in claim 1 or 2, wherein each of said guide plates is connected to both of said transition pieces between which said guide plate is located.

4. A combustor of a gas turbine as claimed in claim 2, wherein radial portions of each of said guide plates are disposed in said gap near the gas outlets of adjacent transition pieces and circumferential portions of each of said guide plates extend circumferentially from the radially outer end of said radial portion to overlie the corners of the radially outer surfaces of gas outlets of adjacent transition pieces.

5. A combustor of gas turbine as claimed in claim 2, wherein each of said guide plates includes a base plate attached to a turbine casing of said gas turbine, and support members fixed to the side walls of said gas outlets of the adjacent transition pieces, each of said support members having a U-shaped channel section for receiving corresponding side edge portion of said base plate.

6. A combustor of a gas turbine as claimed in claim 4, wherein the clearance between said circumferential portion of said guide plate and said radially outer surface of said gas outlet of said transition piece is adjustable to provide the optimum cooling effect.

7. A combustor of a gas turbine as claimed in claim 5, wherein the state of fit of said U-shaped channel sections base plate in said of said support members is so selected as to permit the thermal expansion and shrinkage of said transition pieces but to suppress the vibration of said transition pieces.