Combustor for a gas turbine engine
Number of patents in Portfolio can not be more than 2000
United States of America
Stats
-
Aug 27, 2024
Grant Date -
N/A
app pub date -
Nov 7, 2023
filing date -
Nov 7, 2023
priority date (Note) -
In Force
status (Latency Note)
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Abstract
A combustor for an aircraft gas turbine engine includes a dome structure, a swirler assembly connected to the dome structure, and a cowl connected to the dome structure and defining a plenum between the dome structure and the cowl, and surrounding the swirler assembly. The cowl includes an airflow opening through an upstream wall portion of the cowl for providing a flow of compressed air into the plenum. In addition, the cowl includes a cowl steam channel therewithin and a plurality of steam injection nozzles that provide a flow of steam from the cowl steam channel into the plenum.
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International Classification(s)
- 2023 Application Filing Year
- F23R Class
- 254 Applications Filed
- 102 Patents Issued To-Date
- 40.16 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 0 Citation Count
- F23R Class
- 0 % this patent is cited more than
- 1 Age
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