Integrated combustor nozzles with continuously curved liner segments
Patent
·
OSTI ID:1892562
An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
- Research Organization:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FE0023965
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Number(s):
- 11,231,175
- Application Number:
- 16/012,412
- OSTI ID:
- 1892562
- Country of Publication:
- United States
- Language:
- English
Investigation of Strip Seal Leakage With Special Focus on Seal Groove Design and Relative Displacement of Sealing Surfaces
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conference | June 2017 |
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