Verdichteranordnungen für einen Gasturbinenmotor
Anmelder: RTX Corporation, Raytheon Technologies Corporation, United Technologies Corporation 🇺🇸
Details
- Veröffentlichungs-Nr.
- EP2592235
- Aktenzeichen
- EP12191265
- Anmeldetag
- 5. November 2012
- Veröffentlichung
- 15. Oktober 2014
- Rechtsraum
- EP
- IPC
- F01D1/04F02C3/107F02K3/06F01D13/00
Abstract
A gas turbine engine (90) includes a low pressure compressor section (18) and a high pressure compressor section (22). A low pressure turbine (34) drives the low pressure compressor section (18). A gear arrangement (62) is driven by the low pressure turbine (34) to in turn drive a fan section (14). A pressure ratio across the low pressure compressor section (18) is between about 4-8 and a pressure ratio across the high pressure compressor section (22) is between about 8-15. A compressor case (66) includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case (64) than the front compressor case portion. A support member (78) extends between the fan section (14) and the front compressor case portion. <img class="EMIRef" id="138787947-iaf01" />
Anmelder
- Firmen
- RTX Corporation
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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