Rocket engine fuel supply system and method for eliminating the POGO effectThe system has a gas volume varying device for varying volume of gas in a propellant supplying circuit (4). The gas volume varying device comprises a hydraulic accumulator (8) having variable level of…DRIVE·Sep 3·1 min readFollowB64G1/401SNECMA [FR]
Threaded rod of a system for deploying a deployable propellant nozzleThe threaded rod (22) has a head supported by a support (24), which is secured to a stationary divergent portion (10). The divergent portion is connected with an electric motor (30). A tip is inserted…DRIVE·May 21·1 min readFollowF02K1/00SNECMA [FR]
Turbomachine with an integrated electrical generatorThe turbojet has an axial compressor with a rear bearing disposed between a casing and a rotor. An electricity generator (60) acting as a generator-starter or as an auxiliary generator includes a stat…DRIVE·May 31·1 min readFollowF01D15/10SNECMA [FR]
Two stiffness device for assembling a bearing on the shaft of a rotary engineThe engine has a low pressure turbine shaft (1) mounted relative to a high pressure turbine shaft (2) and comprising a cage winding (5). The winding has two fixing points fixed to a bearing (3) and a …DRIVE·May 3·1 min readFollowF01D25/164SNECMA [FR]
Variable area nozzle for turbomachineThe nozzle has a control system for controlling movable flaps (12a, 12b, 13). The system has control levers composed of controlled levers (16a) directly actuated by jacks (18) and follower levers (16b…DRIVE·May 3·1 min readFollowF02K1/1207SNECMA [FR]
Turbojet engine with a monobloc arm for the connexion of subsidiariesThe turbofan has a monoblock arm (28) comprising support connectors (29) disposed parallel to a radial arm. Each connector connects a support situated outside an outer casing (2) with another support …DRIVE·Mar 29·1 min readFollowF01D25/162SNECMA [FR]
Turbomachine with counter-rotating fanThe turbomachine has a front fan shaft (34) which is connected to an upstream end (24a) of a low-pressure shaft (24) by utilizing a dismountable torque transmission sleeve (48). The sleeve and the sha…DRIVE·Feb 15·1 min readFollowF01D25/16SNECMA [FR]
Degassing pipe for low pressure turbine shaftThe tube has a metallic hollow tubular part with an outer surface covered on a part of its length using a composite material with fibers (20). The fibers are oriented along a longitudinal direction in…DRIVE·Feb 15·1 min readFollowF01D25/20SNECMA [FR]
A turbine engine assembly of a nose cone and a shaft with fan bladesThe bullet (24) is mounted on a shaft (10) by controlled units including a hydraulic jack (42) that displaces the axial position of the bullet with respect to fan blades (18). The cylinder of the jack…DRIVE·Feb 1·1 min readFollowF02C7/042SNECMA [FR]
Jet engine convergent nozzleThe nozzle has controlled and follower flaps (14, 16) made up of composite ceramic matrix material. Each flap is formed as a single unit with cylindrical parts (20, 22) on a peripheral sealing joint a…DRIVE·Feb 1·1 min readFollowF02K1/12SNECMA [FR]
Turbomachine with a protective screen for the fuel manifold of an annular burnerThe engine has a primary air flow reheat pipe with an annular burner (4) having a ring shaped afterburner flame holder gutter (5) whose upstream part is in a secondary air flow. The gutter has a fuel …DRIVE·Jan 25·1 min readFollowF02K3/11SNECMA [FR]
Method for braking aircraft and turbo fan jet engine for implementing the methodThe method involves discharging a part of a secondary air stream to reduce residual thrust of a turbofan (1). The air stream is discharged using a radial opening unit of an engine nacelle (9). The ope…DRIVE·Dec 28·1 min readFollowB64C7/02SNECMA [FR]
Control system and method to control the air flow in a gas turbineThe system has processing systems (20, 30) to calculate control signals (SC20, SC30) based on set point values different from a value (VC10) which is representative of distance in a gas turbine. A sel…DRIVE·Dec 21·1 min readFollowF01D11/24SNECMA [FR]
Method and system for the protection of fuel nozzles in a gas turbine engineThe method involves injecting compressed air in a fuel supply circuit of a fuel injector (7), when a turbine engine (1) is stopped and fuel supply to fuel injection heads of the injector is stopped. T…DRIVE·Dec 14·1 min readFollowF02C7/232SNECMA [FR]
Jet engine casing with fluid conduit and device for attaching the fluid conduit in the jet engine casingThe device has a ring (31) screwed in an opening of a casing (2), and an annular edge (33) supported on a thrust washer (34) at an end of a manifold (12). A nut is screwed into the end of the manifold…DRIVE·Nov 9·1 min readFollowF02K3/11SNECMA [FR]
Mounting device for a burner ring inside a postcombustion chamber of a turbo-jet engineThe device has a locking part (52) engaged between plates (34, 36) and between ends of sectors forming a spray ring. The ends are immobilized between the plates by the part, where the plates are paral…DRIVE·Nov 9·1 min readFollowF01D25/246SNECMA [FR]
Air and fuel delivery system for a post combustor burning ringThe device has distributing cases housed in sectors (38) of a spray ring (26), where air is supplied to the cases through one of their ends extending inside an afterburner flame holder arm (14). The d…DRIVE·Nov 9·1 min readFollowF02K3/11SNECMA [FR]
Device for axially supporting the strut of a stator ring of the high-pressure turbine of a turbomachineThe device includes a longitudinally-extending sheet metal piece (46) constituting a heat shield arranged upstream from the upstream radial wall (18) of a spacer sector (16) against the inner surface …DRIVE·Sep 21·1 min readFollowF01D11/20SNECMA [FR]
Device and method for providing ignition to a post-combustor for bypass gas turbineThe method involves guiding a fraction of primary flow (10) in an ignition zone (34) of an afterburner in order to maintain the temperature in the zone at a value greater than value of secondary flow …DRIVE·Sep 21·1 min readFollowF02K1/386SNECMA [FR]
Support bracket for turboprop engine nozzleThe bridge has two legs (5A, 5B), each constituting an end of a metal blade and contacting a thermal plastic liner. An arched central portion (8) connects the legs and constitutes a zone of contact wi…DRIVE·Sep 21·1 min readFollowF01D25/24SNECMA [FR]
