Konfiguration eines Wellenlagers einer Gasturbine
Anmelder: United Technologies Corporation 🇺🇸
Details
- Veröffentlichungs-Nr.
- EP3081768
- Aktenzeichen
- EP15199861
- Anmeldetag
- 14. Dezember 2015
- Veröffentlichung
- 5. Juni 2019
- Erteilung
- 5. Juni 2019
- Rechtsraum
- EP
- IPC
- F01D25/16F02K3/06F02C3/107F02C7/06F02C7/36F01D25/24F01D25/18
Abstract
A gas turbine engine (20) includes a core housing (60) that has an inlet case (62) and an intermediate case (64) that respectively provide an inlet case flow path (63) and an intermediate case flow path (65). The shaft (40) supports a compressor section (24) that is arranged axially between the inlet case flow path (63) and the intermediate case flow path (65). A geared architecture (48) is coupled to the shaft (40), and a fan (42) coupled to and rotationally driven by the geared architecture (48). The geared architecture (48) includes a sun gear (86) supported on the second end. A first bearing supports (70) the shaft (40) relative to the intermediate case (64) and a second bearing (112) supporting the shaft (40) relative to the inlet case (62). The second bearing (112) is arranged radially outward from the shaft (40).
Anmelder
- Firma
- 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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