PRATT & WHITNEY CANADA CORP.
|PRATT & WHITNEY CANADA CORP. Patent applications|
|Patent application number||Title||Published|
|20150251770||SYSTEM AND METHOD FOR OPERATING A MULTI-ENGINE AIRCRAFT IN AN AUXILIARY POWER UNIT MODE - A first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with a selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.||09-10-2015|
|20150247641||COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE AND METHOD OF OPERATING SAME - A gas turbine engine comprises a combustion system comprising a secondary annular combustor and a primary combustor in fluid communication with the secondary combustor, a secondary fuel injector associated with the secondary combustor, a primary fuel injector associated with the primary combustor, and a ECU controlling fuel delivery to the secondary and primary fuel injectors. The primary fuel injector delivers fuel to the primary combustor. The ECU allows fuel to be delivered to the secondary fuel injector in addition to the primary fuel injector only when a fuel amount higher is requested delivered by the primary fuel injector. A method of operating a gas turbine engine is also presented.||09-03-2015|
|20150247420||FLAPPER VALVE ASSEMBLY AND METHOD OF FLOWING AIR THERETHROUGH - A valve assembly for a gas turbine engine comprising two flappers movable independently from one another between an open position and a closed position; and a fairing disposed between the two flappers. The fairing has a portion extending downstream of the two flappers. The portion is a downstream portion of a substantially streamlined body. The two flappers are movable relative to the fairing, and when in the open position, the two flappers abut the fairing and form an upstream portion of the substantially streamlined body. A method of flowing air through a valve assembly for a gas turbine engine is also presented.||09-03-2015|
|20150247419||TURBINE BLADE FOR A GAS TURBINE ENGINE - A turbine blade for a gas turbine engine comprises an airfoil having a pressure side, a suction side, a span direction and a chord-wise direction. The airfoil has an airfoil span on a pressure line being a projection of the stacking line onto the pressure side. The airfoil has a plurality of chords extending between a leading edge and a trailing edge of the airfoil. A generally round dimple is disposed on the pressure side. The dimple is contained in an area extending on the stacking line between 0% and 23% of the airfoil span from the inner end, and in the chord-wise direction between 0% of a first chord and 82% of a second chord from the leading edge. The dimple is configured to initiate fracture of the blade at a predetermined speed of rotation. A method of preventing rupture of a disk of a turbine rotor is also presented.||09-03-2015|
|20150247407||POWER TURBINE BLADE AIRFOIL PROFILE - A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.||09-03-2015|
|20150246371||METHOD OF COLD SPRAYING COMPONENTS OF A GAS TURBINE ENGINE MASK THEREFOR - A method of cold spray coating a target surface of a component, the coating provided using selected solid powders, the method comprising: placing a mask onto the component to cover an area of the component adjacent the target surface which is not to be coated, the mask having a masking top surface provided of a material selected to be non-adhesive with the selected solid powders when cold-sprayed onto the masking top surface, the mask having a melting point above a temperature at which cold spray is performed; cold spraying the target surface with the selected solid powders, including at least some overspraying onto the mask; removing the overspray from the mask; and removing the mask from the component. A mask for a cold sprayed component of a gas turbine engine is also presented.||09-03-2015|
|20150241309||COMPONENT OF A GAS TURBINE ENGINE AND METHOD OF DETECTING A CRACK THEREIN - A component of a gas turbine engine comprises a substrate, a corrosion resistant top layer, and an intermediate corrodible layer disposed between the corrosion resistant top layer and the substrate. When corroding, the intermediate layer has a color contrasting with a color of the top layer. A method of detecting a crack when it penetrated the top layer in a component of a gas turbine engine having a corrosion resistant top layer and an intermediate corrodible layer comprises, in sequence, observing that at least one area of the component has a color contrasting with that of the top layer; determining that the color of the at least one area is a result of corrosion of the intermediate corrodible layer; and determining that the top layer has a crack as a result of determining corrosion of the intermediate layer. A method of facilitating crack detection in a component is also presented.||08-27-2015|
|20150240976||MOVEMENT-CONSTRAINING ASSEMBLY FOR FLUID-CONVEYING SYSTEM - A movement-constraining assembly for a fluid-conveying system comprises a fluid-conveying tube defining an inner passage for fluid to pass therethrough. The tube is adapted to be connected to components of the fluid-conveying system at opposed ends thereof. A blocking ring is mounted to the tube with complementary surfaces between the tube and the blocking ring to block rotation between the tube and the blocking ring, the blocking ring having a first joint portion. A base is adapted to be secured to a structure, and having a second joint portion operatively joined to the first joint portion of the blocking ring to form a joint blocking at least an axial rotational degree of freedom of the fluid-conveying tube and allowing at least one translational degree of freedom of the tube relative to the structure. A method for constraining movement of a fluid-conveying tube of a fluid conveying-system is also provided.||08-27-2015|
|20150240721||AIRCRAFT COMPONENTS WITH POROUS PORTION AND METHODS OF MAKING - A component including a porous portion which may be permeable or impermeable to air, and a method for making. In one example, the component is a cooled wall segment for a gas turbine engine, including a body defining a contact surface configured to be in contact with circulating hot gas and an outer surface configured to be in contact with cooling air. The body includes a first portion with at least one retention element, and a porous second portion made of a porous material permeable to air, containing a plurality of interconnected pores, and having a porosity greater than that of the first portion. The second portion is engaged to the first portion, defines at least part of the contact surface, and defines at least part of a fluid communication between the outer surface and the contact surface through the interconnected pores. The wall segment may be for example a heat shield or shroud segment. Methods of forming components are also discussed.||08-27-2015|
|20150239010||METHOD OF FORMING AN ABRADABLE COATING FOR A GAS TURBINE ENGINE - A method of forming an abradable coating on a gas turbine engine component comprising, in sequence: placing dry lubricant particles and trapping particles in a channel having a spraying end and containing a gas; causing at least one shockwave in the gas to travel in the channel toward the spraying end, the at least one shockwave causing the dry lubricant particles and the trapping particles to travel in the channel with it, the at least one shockwave reducing interparticle spacing and increasing particles density; directing a resulting flow of the dry lubricant particles and the trapping particles from the spraying end at a supersonic velocity to impact the component; and then plastically deforming the trapping particles upon impacting the component with the resulting flow thereby trapping the dry lubricant particles with the deformed trapping particles onto the component to provide the abradable coating.||08-27-2015|
Patent applications by PRATT & WHITNEY CANADA CORP.