Inventor

Gerard E. A. Jourdain

Inventor

Saintry sur Seine, FR

Overview

30→

Patents

1983–2001

Patent span

Mechanical engineering

Primary field (CPC F)

Patents· 30 as inventor

Public. Assignee & technology derived from the patent record. Each patent links to its LexDana page.

Y02Tprimary

Y02TClimate change mitigation technologies related to transportation22%

F02KJet-propulsion plants20%

F01DNon-positive displacement machines or engines, e.g. steam turbines11%

F05DIndexing scheme for aspects relating to non-positive-displacement machines or engines, gas-turbines or jet-propulsion plants11%

F23RGenerating combustion products of high pressure or high velocity, e.g. gas-turbine combustion chambers9%

F02CGas-turbine plants7%

B29CShaping or joining of plastics3%

F04DNon-positive-displacement pumps3%

Y10STechnical subjects covered by former uspc cross-reference art collections [xracs] and digests3%

Y10TTechnical subjects covered by former us classification3%

PatentTitleYear

6,276,126'Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle'2001 6,185,926'Turbojet engine thrust reverser and exhaust nozzle assembly'2001 6,082,669'System for the admission of air into a working section of a gas turbine engine'2000 5,934,564'Variable geometry turbojet engine exhaust nozzle'1999 5,623,821'Turbojet equipped with a deicing system on the intake case'1997 5,593,278'Gas turbine engine rotor blading sealing device'1997 5,566,884'Supersonic nozzle for a turbojet engine'1996 5,542,607'Supersonic nozzle, in particular for a turbojet engine'1996 5,520,336'Nozzle for a jet engine containing an adjustable convergent-divergent portion'1996 5,421,704'Inter-blade platform for a bladed disc of a turbomachine rotor'1995 5,367,874'Integral composite gas turbine afterburner structure'1994 5,359,849'Afterburner assembly for a gas turbine engine'1994 5,269,138'Variable geometry flame trap device for use in an after-burner device of a gas turbine'1993 5,263,823'Gas turbine engine impeller having an annular collar platform'1993 5,193,982'Separate inter-blade platform for a bladed rotor disk'1993 5,116,218'Segmented hot molding apparatus'1992 5,069,034'Heat protective lining for an afterburner or transition duct of a turbojet engine'1991 4,974,638'Transition pipe for a jet pipe assembly of a turbojet engine'1990 4,955,541'Two dimensional nozzle for a turbojet engine'1990 4,907,743'Assembly of two bodies having distinctly different coefficients of expansion'1990 4,817,871'Control system for turbojet engine nozzle flaps'1989 4,805,398'Turbo-machine with device for automatically controlling the rate of flow of turbine ventilation air'1989 4,778,109'Adjustable two dimensional nozzle for aircraft jet engines'1988 4,716,640'Method for manufacturing a burner ring for a turbojet engine'1988 4,679,982'Compressor blow-off arrangement'1987 4,674,951'Ring structure and compressor blow-off arrangement comprising said ring'1987 4,565,492'Sealing device for turbine blades of a turbojet engine'1986 4,546,606'Pressure drop regulating device'1985 4,541,567'Variable area nozzle vane'1985 4,409,791'Injection device for the combustion chamber of turbine engines'1983

Career & activity timeline

Assembled from patent assignee/location history and declaration credentials.

1983–2001Patents assigned to SNECMA (27)· patent assignee history

1983–2001Based in Saintry sur Seine, FR· patent location history

1987Patents assigned to METEUR D A SOC NAT D ETUDE CON (1)· patent assignee history

1988–1990Based in Corbeil Essonnes, FR· patent location history

1989Patents assigned to CONSTURCTION DE MOTEURS D AVIA (1)· patent assignee history

2001Patents assigned to SNECMA MOTEURS (1)· patent assignee history

Inventor activity

Assignee and location history derived from the patent record.

Assignees

Assignee	Patents	Span
SNECMA	27	1983–2001
CONSTURCTION DE MOTEURS D AVIA	1	1989
METEUR D A SOC NAT D ETUDE CON	1	1987
SNECMA MOTEURS	1	2001

Locations

Location	Patents	Span
Saintry sur Seine, FR	25	1983–2001
Corbeil Essonnes, FR	5	1988–1990