Patent · US Expired

Compressor turbojet engine whose rotor has a movable upstream stage

US5473883A · kind A · utility

14Cited by

4References

8Claims

0Family size

Assignee

Societe Nationale d'Etude et de Construction de Moteurs d'Aviation - S.N.E.C.M.A · FR

Inventor

Jacky Naudet · Bondoufle, FR

Key dates

Filing date	Nov 1, 1994
Grant date	Dec 12, 1995
Priority date	—
Expiry date	Nov 1, 2014

Classification

Technology area (CPC F)Mechanical Engineering; Lighting; Heating
CPC primaryF05D2230/70
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

Turbojet engine compressor . . . Its rotor (43) includes a movable end portion (45), such as a monoblock vaned disk able to be removed and replaced by a block. High and low pressure shaft lines (54) are formed into several portions to enable these operations to take place without having to dismantle the entire engine.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.