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Transition duct system with a robust joint at an intersection between adjacent converging transitions ducts extending between a combustor and a turbine assembly in a gas turbine engine

A piping system and piping technology, applied in the direction of gas turbine installations, engine manufacturing, engine components, etc., can solve problems such as crack development, weakening material properties, damage guide vanes and associated support structures, etc., to eliminate leakage, eliminate need, increase size Effect

Inactive Publication Date: 2017-02-22
SIEMENS ENERGY INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The forces and heat involved weaken the material properties, causing cracks to develop and otherwise damage the vanes and associated support structures

Method used

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  • Transition duct system with a robust joint at an intersection between adjacent converging transitions ducts extending between a combustor and a turbine assembly in a gas turbine engine
  • Transition duct system with a robust joint at an intersection between adjacent converging transitions ducts extending between a combustor and a turbine assembly in a gas turbine engine
  • Transition duct system with a robust joint at an intersection between adjacent converging transitions ducts extending between a combustor and a turbine assembly in a gas turbine engine

Examples

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Embodiment Construction

[0041] as in Figure 11-Figure 21 As shown in , a transition duct system 110 in a combustion turbine engine 118 is disclosed for directing the flow of combustion exhaust gas from a combustor 112 to a first stage 114 of a turbine section 116 whereby the system 110 imparts peripheral Combustion exhaust gases exiting the system 110 are vectored, thus eliminating the need for a conventional first row vane assembly. The transition duct system 110 may include a robust convergent flow junction 120 between adjacent transition ducts 122 , 124 within the system 110 such that adjacent transition sections 122 , 124 may be joined to each other via a junction 126 forming a linear edge 128 , which provides a solid, robust interface between adjacent transition sections 122 , 124 . In at least one embodiment, the linear edge 128 at the junction 126 may be within 10 degrees of being perpendicular to the inner edge 130 of the transition sections 122, 124 at the junction 126, as in Figure 14 w...

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PUM

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Abstract

A transition duct system (110) for routing a combustion exhaust gas flow from a combustor (112) to the first stage (114) of a turbine section (116) in a combustion turbine engine (118) is disclosed, whereby the system (110) imparts a circumferential vector to the combustion exhaust gases expelled from the system (110), thereby negating the need for a conventional row one vane assembly. The transition duct system (110) may include a robust converging flow joint between adjacent transition ducts (122, 124) within the system (110) such that adjacent transition sections (116) may be adjoined to each other via an intersection (126) forming a linear edge (128) which provides for a strong robust intersection (126) between the adjacent transition sections (116). In at least one embodiment, the linear edge (128) at the intersection (126) may be within 10 degrees of being orthogonal to an inner edge (130) of the transition sections (116) at the intersection (126).

Description

[0001] Statement Regarding Federally Funded Research and Development [0002] The development of this invention was supported in part by the U.S. Department of Energy, Advanced Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the US Government may have certain rights in this invention. technical field [0003] The present invention relates generally to gas turbine engines, and more particularly to transition ducts for directing gas flow from a combustor of a gas turbine engine to a turbine section. Background technique [0004] In a conventional gas turbine engine, as in figure 1 As shown in , combustion gases generated within the combustor 10 are passed to the turbine assembly via a plurality of transition ducts 12 . In many conventional systems, the transition duct 12 extends longitudinally without any offset in the circumferential direction. A row of first stage vanes 14 is used to divert the combustion exhaust gases before passing them to a fi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02
CPCF01D9/023F01D5/02F02C3/14F05D2220/32F05D2240/35F05D2250/314
Inventor J.W.哈德斯
Owner SIEMENS ENERGY INC