EP 1739309 A1 20070103 - Multi stage turbomachine compressor
Title (en)
Multi stage turbomachine compressor
Title (de)
Mehrstufiger Turbomaschinenkompressor
Title (fr)
Compresseur multi-étages de turbomachine
Publication
Application
Priority
FR 0506610 A 20050629
Abstract (en)
The compressor has multiple compression stages, each with annular rows of movable blades (12) rotating inside a double wall casing (18), and annular rows of straightened fixed blades (14) carried by an inner wall of the casing. The inner wall is formed of integrated ferrules (30, 32) aligned end-to-end and independently suspended to an outer wall (20) of the casing by edge springs (34, 36). The ferrules (30, 32) respectively surround the annular rows of movable blades and the annular rows of straightened fixed blades. An independent claim is also included for a jet prop engine or jet engine of aircraft.
IPC 8 full level
F01D 11/16 (2006.01); F04D 29/16 (2006.01)
CPC (source: EP US)
F04D 29/164 (2013.01 - EP US)
Citation (search report)
- [X] US 5630702 A 19970520 - MARMILIC ROBERT [CH], et al
- [X] US 4522559 A 19850611 - BURGE JOSEPH C [US], et al
- [X] US 5351478 A 19941004 - WALKER ROGER C [US], et al
- [A] FR 2688539 A1 19930917 - SNECMA [FR]
- [A] US 6390771 B1 20020521 - GERVAIS PASCAL GERARD [FR], et al
Designated contracting state (EPC)
DE FR GB
Designated extension state (EPC)
AL BA HR MK YU
DOCDB simple family (publication)
EP 1739309 A1 20070103; EP 1739309 B1 20170111; FR 2887939 A1 20070105; FR 2887939 B1 20160930; RU 2006123033 A 20080110; RU 2375607 C2 20091210; US 2009304498 A1 20091210; US 7651317 B2 20100126
DOCDB simple family (application)
EP 06291053 A 20060626; FR 0506610 A 20050629; RU 2006123033 A 20060628; US 47611306 A 20060628