Gas turbine combustor exit piece with hinged connections
An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
- Research Organization:
- SIEMENS ENERGY, INC., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- Patent Number(s):
- 9,322,335
- Application Number:
- 13/834,185
- OSTI ID:
- 1248880
- Resource Relation:
- Patent File Date: 2013 Mar 15
- Country of Publication:
- United States
- Language:
- English
Similar Records
Structural support bracket for gas flow path
An experimental/computational study of airflow in the combustor-diffuser system of a gas turbine for power generation