Patent application number | Description | Published |
20080273967 | Ring seal for a turbine engine - A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks. | 11-06-2008 |
20080298973 | Turbine vane with divided turbine vane platform - A turbine vane with endwalls, wherein at least one endwall is formed from two or more sections configured such that the sections form releasable joints with a generally elongated airfoil of the turbine vane. The sections may be configured to both support the generally elongated airfoil and to establish cooling fluid flowpaths between the sections and the generally elongated airfoil to cool the aspects of the turbine vane proximate to the intersection of the endwalls and the generally elongated airfoil. In addition, the joints between the generally elongated airfoil and the sections may be formed from a connection system that enables forces to be transmitted from the generally elongated airfoil to the endwalls without creating stresses found in conventional turbine vane fillets at the intersection between the generally elongated airfoil and the endwalls. | 12-04-2008 |
20090014926 | Method of constructing a hollow fiber reinforced structure - A method of constructing a hollow fiber reinforced structure is disclosed. A spindle structure is provided for defining a preform shape. A resin binder or matrix is applied to a fiber material and the fiber material is placed around the spindle structure to create a hollow preform having a shape defined by the spindle structure. The preform structure is reshaped into a desired shape defined by the interior surface of a hollow mold and the exterior surface of an expandable insert structure. The reshaped preform structure is further conditioned to create a finished part. A hollow filament wound ceramic matrix composite airfoil suitable for use in a gas turbine engine may be constructed using the disclosed method. | 01-15-2009 |
20090053037 | TURBINE VANES WITH AIRFOIL-PROXIMATE COOLING SEAM - Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life. | 02-26-2009 |
20100062210 | CERAMIC MATRIX COMPOSITE STRUCTURE - A composite structure ( | 03-11-2010 |
20120148794 | CMC ANCHOR FOR ATTACHING A CERAMIC THERMAL BARRIER TO METAL - A ceramic matrix composite (CMC) anchor ( | 06-14-2012 |
20130121806 | EXHAUST DIFFUSER FOR A GAS TURBINE, AND METHOD THEREOF - An exhaust diffuser assembly is provided, particularly for a stationary gas turbine. The exhaust diffuser assembly includes a longitudinal axis, a diffuser inlet for receiving a turbine mainflow gas, a diffuser outlet, and a diverging diffuser wall having an adjustable geometry and forming a conduit for flow of the gas therethrough from the diffuser inlet to the diffuser outlet. The diffuser wall has a divergence angle ‘α’ with respect to the longitudinal axis. The diffuser assembly also has a diffuser geometry control device for controlling a recovery of pressure from the gas between the diffuser inlet and the diffuser outlet by adjusting the divergence angle ‘α’ of the diffuser wall to cause a resultant flow field of the gas that is attached to the diffuser wall. | 05-16-2013 |
20130227954 | GAS TURBINE ENGINE CONFIGURED TO SHAPE POWER OUTPUT - A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid. | 09-05-2013 |
Patent application number | Description | Published |
20110084168 | REMOVABLE BACK SHELL FOR AN AIRCRAFT SEAT - An aircraft seat that includes a seat bottom frame having a back, a seat back frame pivotally connected to the back of the seat bottom frame, and a seat back shell. The seat back shell has at least a front panel, a back panel opposite the front panel, and at least two side panels disposed between the front and back panels which connects the front panel to the back panel. The combination of the front, back, and side panels form a gap to receive the entire seat back frame. | 04-14-2011 |
20110084527 | AIRCRAFT SEAT CONTROL INPUT TRANSFER AND DISCONNECT MECHANISM - An aircraft seat includes a seat bottom frame, a seat translation and rotation mechanism attached to the seat bottom frame allowing translation and rotational movement of the seat bottom frame. An armrest is removably attached to the side of the seat bottom frame, and can be set to different positions relative to the seat bottom. The armrest has a seat control mounted to an outside of the armrest, and an input transfer mechanism disposed inside the armrest. The input transfer mechanism has an end engaged to the seat control, and a receiver end. The input transfer mechanism is cable-less. A couple shaft is engaged with the receiver end and engaged with the seat translation and rotation mechanism. When the seat control is actuated, the input transfer mechanism causes the seat translation and rotation mechanism to allow the seat bottom frame to at least one of translate and rotate. | 04-14-2011 |
20130154329 | REMOVABLE BACK SHELL FOR AN AIRCRAFT SEAT - An aircraft seat that includes a seat bottom frame having a back, a seat back frame pivotally connected to the back of the seat bottom frame, and a seat back shell. The seat back shell has at least a front panel, a back panel opposite the front panel, and at least two side panels disposed between the front and back panels which connects the front panel to the back panel. The combination of the front, back, and side panels form a gap to receive the entire seat back frame. | 06-20-2013 |
20130241256 | AIRCRAFT SEAT CONTROL INPUT TRANSFER AND DISCONNECT MECHANISM - An aircraft seat includes a seat bottom frame, a seat translation and rotation mechanism attached to the seat bottom frame allowing translation and rotational movement of the seat bottom frame. An armrest is removably attached to the side of the seat bottom frame, and can be set to different positions relative to the seat bottom. The armrest has a seat control mounted to an outside of the armrest, and an input transfer mechanism disposed inside the armrest. The input transfer mechanism has an end engaged to the seat control, and a receiver end. The input transfer mechanism is cable-less. A couple shaft is engaged with the receiver end and engaged with the seat translation and rotation mechanism. When the seat control is actuated, the input transfer mechanism causes the seat translation and rotation mechanism to allow the seat bottom frame to at least one of translate and rotate. | 09-19-2013 |
20130328371 | REMOVABLE BACK SHELL FOR AN AIRCRAFT SEAT - An aircraft seat that includes a seat bottom frame having a back, a seat back frame pivotally connected to the back of the seat bottom frame, and a seat back shell. The seat back shell has at least a front panel, a back panel opposite the front panel, and at least two side panels disposed between the front and back panels which connects the front panel to the back panel. The combination of the front, back, and side panels form a gap to receive the entire seat back frame. | 12-12-2013 |
20140239683 | AIRCRAFT SEAT ENERGY ABSORBING DEVICE FOR OCCUPANT RESTRAINT - An energy absorbing device for a seat containing an occupant includes a seat frame with legs, a seat pan, and a back member. Attached to the seat is an energy absorbing device fixed to the back member of the seat frame. The energy absorbing device includes an engagement portion fixing the energy absorbing device to the seat frame and an energy absorbing extension having a fixed end integral with the engagement portion, and a protruding end extending toward the seat pan. The seat has a seat belt for the occupant and the belt is attached to a belt support device which extends parallel to the energy absorbing extension. When the occupant is using the seatbelt and the seat undergoes lateral forces, the energy absorbing extension undergoes deformation, and when the occupant is not using the seatbelt and the seat undergoes lateral forces, the energy absorbing extension does not undergo deformation. | 08-28-2014 |
20140265511 | DOUBLE SPRING LEG REST - A vehicle seat can include a seat bottom frame having a front, a back opposite the front, and enclosing a volume. Pivotally connected to the back of the seat bottom frame can be a seat back frame and pivotally connected to the front of the seat bottom frame can be a seat leg rest. The seat leg rest has a length. Mounted in the volume of the seat frame are at least two leg rest springs which are connected to the leg rest. When the leg rest springs are actuated, the seat leg rest can be directly pivoted approximately and incrementally parallel with the seat bottom frame. The two leg rest springs are mounted a first distance apart and the first distance is less than half of the length of the leg rest. | 09-18-2014 |