An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.

A planetary gear train speed reduction gear planetary carrier (130) assembly and an elastically deformable annular member (160), for a turbine engine, in particular for an aircraft. The planetary carrier (130) has a general annular shape about an axis X. The annular member (160) extends about the axis X, and is fixed to the planetary carrier and configured to be fixed to a stator element (162) of the turbine engine ensuring a flexible connection between the planetary carrier and the stator element. The planetary carrier carries a series of protruding teeth (180) extending substantially radially outwards with respect to the axis X. Each of these teeth has first opposite side faces (180a, 180b) extending into planes passing through the axis X capable of engaging by abutment in the circumferential direction with the stator element. A vibration absorption system is inserted between the first faces and the stator element.

The present disclosure provides a method for manufacturing a preform made of reinforcement fibers woven in a longitudinal direction. The preform is impregnated with resin in order to form an elongated element having a variable transverse cross-section. In one form, the method includes the step of simultaneously including a reduction (or increase) in width and an increase (or reduction) in height. The variable cross-section includes, along the length thereof, a consistent number (c) of continuous warp threads arranged in layers. The method for reducing width includes carrying out a change in weave, adding additional weft threads, and simultaneously drawing the teeth of the longitudinal beater reed closer together so as to increase the number of layers.

A de-icing system for one or more vanes of a gas turbine engine. The system comprises a coating of electrically conductive material on at least a portion of a vane and a plurality of magnets located circumferentially about a rotor shaft of the gas turbine engine and configured to be driven by the rotor shaft in the circumferential direction to generate a rotating magnetic field. A coiled wire is configured to remain stationary within the rotating magnetic field so as to induce a current therein, the coiled wire being connected to the coating for supplying the induced current to the electrically conductive material. In this way, the coating of electrically conductive material is heated by the induced current, for inhibiting ice accretion on the vane.

A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

A catch assembly is provided that includes a keeper, a guide and a catch. The catch includes a catch mount, a catch arm and a catch hook. The catch arm is cantilevered from the catch mount. The catch arm extends longitudinally away from the catch mount to a distal end of the catch. The catch hook is connected to the catch arm at the distal end. The catch is configured to bias the catch hook against the guide. The catch hook is configured to slide longitudinally along the guide from a first position to a second position where the catch hook engages the keeper.

The present invention provides a method for distributing relative gap parameters of large-scale high-speed rotary equipment components based on eccentricity vector following measurement and adjustment. According to the present invention, a propagation process of location and orientation errors of rotors and stators of an aero-engine during assembly are analyzed, a propagation relationship of eccentricity errors after n-stage rotor and stator assembly is determined, and a coaxiality prediction model after multi-stage rotor and stator assembly is obtained; and the relative concentricity and relative runout of the rotors and stators can be further obtained by using an offset of the rotors and stators, thereby implementing the calculation of a relative gap; thereafter, a dual-objective optimization model for multi-stage rotor and stator coaxiality and relative gap amount based on an angular orientation mounting position of all stages of rotors and stators is established, the angular orientation mounting position of all stages of rotors and stators is optimized by using a genetic algorithm, to obtain an optimal mounting phase of all stages of rotors and stators; and finally, relative gap parameters of the rotor and stator can be distributed by using a probability density method.

Disclosed is a vane assembly. An outer ring segment surrounds a rotor extending through an inner central portion of a casing. Vanes are fitted into the outer ring segment in a direction perpendicular to an axial direction of the rotor. A fixing portion is fitted into the outer ring segment to fix the vanes to the outer ring segment.

A nacelle for a gas turbine engine includes at least one hinge axis extending along the nacelle. At least one cowl is mounted to the nacelle, along the at least one hinge axis, by a plurality of hinges. The plurality of hinges includes at least one latch. The at least one latch includes a clevis and a tang. The clevis and the tang of the at least one latch are configured to receive a hinge pin, through a pin aperture, when the at least one cowl is in a closed condition.

A gas turbine engine includes a compressor section having a first portion and an aft portion. A compressor case clearance (CCC) control system is configured to adjust an amount of bleed air delivered to the front portion and the aft portion based on an in-flight phase of an aircraft. In response to invoking a first mode, the CCC control system delivers air to both the front portion and the aft portion. In response to invoking a second mode, the CCC control system reduces the amount of air delivered to the aft portion prior to transitioning from the cruise phase to the descent phase. Accordingly, clearance areas within the compressor section can be selectively increased during specific portions of the flight to avoid contact between blade tips and the engine case.