Modulierter Brennkammer-Bypass und Brennkammer-Bypassventil
Anmelder: Raytheon Technologies Corporation, United Technologies Corporation 🇺🇸
Details
- Veröffentlichungs-Nr.
- EP3508790
- Aktenzeichen
- EP19150786
- Anmeldetag
- 8. Januar 2019
- Veröffentlichung
- 21. April 2021
- Erteilung
- 21. April 2021
- Rechtsraum
- EP
- IPC
- F23R3/26F01D17/14F02C9/18
Abstract
A combustor section (26) of a gas turbine engine (20) includes a combustor (56) having a combustor inlet (62), and a combustor bypass passage (64) having a passage inlet (66) located upstream of the combustor inlet, the combustor bypass passage configured to divert a selected bypass airflow (70) around the combustor. A combustor bypass valve (72) is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. The combustor bypass valve including a valve element (80) configured to rotate about an engine central longitudinal axis (A) to move one or more valve openings (82) relative to one or more bypass passage openings (67).
Anmelder
- Firmen
- Raytheon Technologies Corporation
United Technologies Corporation - Land
- 🇺🇸 USA
US-amerikanischer Luft- und Raumfahrt- sowie Verteidigungskonzern, entstanden aus Raytheon und United Technologies. Entwickelt und fertigt Triebwerke, Avionik, Radarsysteme, Raketen- und Verteidigungstechnik für zivile und militärische Kunden.
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