Liquid-cooled transition member to turbine inlet

• US 4,195,474 A
• Filed: 10/17/1977
• Issued: 04/01/1980
• Est. Priority Date: 10/17/1977
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bintz, Miles F., Dehmer, deceased, Raymond L.
• Primary Examiner(s): Croyle, Carlton R.
• Assistant Examiner(s): Ross, Thomas I.
• Application Number:
  US05/842,400
• Time in Patent Office: 897 Days
• Field of Search: 60/39.66, 60/267, 165/169, 165/173, 165/175, 165/176, 165/51, 415/116, 415/175, 415/176
• US Class Current: 60/730
• 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

Abstract

An improved structure is provided for liquid cooling a transition member which conducts hot motive gases from a combustor to a turbine inlet in a gas turbine power plant. The liquid-cooled structure includes a transition member body having a longitudinal inlet manifold and a longitudinal collection manifold attached to opposite sides of the body. The body has a plurality of internal laterally disposed passages which communicate liquid coolant from the inlet manifold, around the body to the collection manifold. The liquid coolant transfers heat from the member in a circumferential flow pattern; then the coolant is discharged from the member by a discharge manifold which is connected to the collection manifold. The method of manufacturing of the transition member provides for forming the body in two mating half subassemblies having internal coolant passages. Each half of the body is blanked from a flat sheet having a shape conforming to the developed shape of the body. Lateral slots are machined on the surface of the sheet. The coolant passages are formed by diffusion bonding a metallic skin over the slotted surface in one method and by embedding tubular members in the slots in an alternate method. The subassemblies are then formed into the contoured shape of the body. The subassemblies and components forming the manifolds are welded together to form the transition member.

Claims

1. In a gas turbine including a combustion liner and a turbine, a transition member for conducting hot combustion gas from the combustion liner to an inlet passage of the turbine, said transition member comprising:

a contoured body having an inlet end of circular cross-section conforming to the shape of the exit end of the combustion liner and an exit end of generally rectangular cross-section conforming to the shape of the turbine inlet passage;

an inlet manifold having an inlet adjacent the inlet of said body adapted to receive liquid coolant, said inlet manifold extending longitudinally along and in intimate contact with said body;

an outlet collection manifold having an outlet adjacent the inlet of said body adapted to exhaust the liquid coolant, said outlet collection manifold extending longitudinally along and in intimate contact with said body;

said body having a plurality of laterally disposed passages communicating liquid coolant between said inlet manifold and said collection manifold for transferring heat from said body to the liquid coolant as the coolant follows a lateral circumferential flow pattern.