Did You Know...
...that when IBM conducted a market study of Chester Carlson's invention in 1959, the company concluded that it would take only 5000 units of his new product to saturate the market? IBM therefore declined to be part of the new product introduction. Too bad for IBM. Carlson's invention was the xerography process, and his new product was the beginning of the Xerox Corporation. It is estimated that every day, worldwide, 3,000,000,000 copies are made!!
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8181467 | Mid-turbine frame torque box having a concave surface A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque... | 05/22/2012 |
| 8181465 | Positioning arrangement for components of a pressure vessel and method The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses. ... | 05/22/2012 |
| 8181466 | Mid-turbine frame A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts... | 05/22/2012 |
| 8171738 | Gas turbine internal manifold mounting arrangement A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold. ... | 05/08/2012 |
| 8141370 | Methods and apparatus for radially compliant component mounting Methods and apparatus for a mounting assembly for a liner of a gas turbine engine combustor are provided. The combustor includes a combustor liner and a radially outer annular flow sleeve. The mounting assembly includes an inner ring surrounding a radially outer sur... | 03/27/2012 |
| 8136362 | Turbomachine fan duct A turbomachine fan duct is disclosed. The fan duct includes two coaxial cylindrical walls, these being an internal wall and an external wall, respectively. The internal wall includes a framework to which panels are removably attached, and the external wall includes ... | 03/20/2012 |
| 8122726 | Combustion chamber of a combustion system A combustion chamber of a combustion system has a combustion space, a support structure, a support element, and a heat shield. The heat shield has at least two segments, and each segment includes a liner element facing the combustion space and has an edge region, a ... | 02/28/2012 |
| 8104290 | Combustion liner damper The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a comb... | 01/31/2012 |
| 8091370 | Combustor liner cap assembly A liner cap assembly is disclosed for use in a gas turbine engine combustor. The assembly includes an outer ring that extends along an axis. Multiple struts are circumferentially arranged about an inner diameter of the outer ring and extend radially inwardly therefr... | 01/10/2012 |
| 8091371 | Mid turbine frame for gas turbine engine A mid turbine frame of a gas turbine engine includes an outer case which supports a spoke casing co-axially positioned therein. The spoke casing has load transfer spokes extending radially from an inner case and secured to the outer case. A load transfer device is p... | 01/10/2012 |
| 8087252 | Turbomachine combustion chamber An annular combustion chamber for a turbomachine is disclosed. The combustion chamber includes radially internal and radially external cylindrical walls which are fixed by bolting at their upstream ends to an internal and an external annular flange of an annular cha... | 01/03/2012 |
| 8001790 | Gas turbine There is provided a gas turbine capable of improving the durability of a main shaft by absorbing the deformation of a casing due to heat and pressure and suppressing stresses acting on the main shaft. A link plate 31 of a movable supporting leg 30 that... | 08/23/2011 |
| 7987678 | Hot gas duct and duct splitter arrangement A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral edge of the duct splitter. At least one, preferably two, of the holdin... | 08/02/2011 |
| 7946119 | Sealing arrangement An arrangement for sealing an opening formed in a wall for receiving a member. The arrangement comprises a sealing member with a passage, and the sealing member is moveably mounted on the wall adjacent to the opening such that the sealing member passage is substanti... | 05/24/2011 |
| 7937950 | Device for fastening a sequentially operated burner in a gas turbine arrangement A device for fastening a second burner (SEV burner) (1) in a sequentially operated gas turbine arrangement, in which a fuel/air mixture is burnt in a first burner, so as to form hot gases which can subsequently be supplied, partly expanded, for a second combu... | 05/10/2011 |
| 7930891 | Transition duct with integral guide vanes A transition duct used in a gas turbine engine to direct the hot gas flow from the combustor into the turbine section of the gas turbine engine. The transition duct includes a plurality of guide vane integral with the duct. The transition duct includes a circular sh... | 04/26/2011 |
| 7874164 | Fuel nozzle flange with reduced heat transfer A fuel nozzle for a gas turbine engine comprises a nozzle body defining a passage extending therethrough and a flange around the nozzle body extending radially and outwardly from the nozzle body. The flange defines a mounting face thereof and a plurality of mounting... | 01/25/2011 |
| 7866162 | Exhaust cone for channeling a stream of gas downstream from a turbine An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially. ... | 01/11/2011 |
| 7861535 | Self-aligning liner support hanger A self-aligning hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a rod, a first ball joint and a second ball joint. The first bracket is for connecting to an exhaust duct of the gas turbine exhaust system. The second... | 01/04/2011 |
| 7836702 | Gas turbine combustor exit duct and HP vane interface An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions locat... | 11/23/2010 |
| 7814753 | Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachm... | 10/19/2010 |
| 7805949 | Device for supporting and housing auxiliaries in a bypass turbojet A device for supporting and housing auxiliaries in a bypass turbojet is disclosed. The device includes two coaxial case rings arranged one inside the other and connected by tubular radial arms through which fluid ducts and electric cables pass. At least one of the r... | 10/05/2010 |
| 7805948 | Internally mounted device for a pressure vessel An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing. ... | 10/05/2010 |
| 7797947 | Mounting assembly for securing an engine to an aircraft wing An engine assembly including an engine mount, the engine mount including a rigid structure including a box and a mounting system positioned between the engine and the rigid structure. This mounting system includes an aft attachment. The assembly further includes a t... | 09/21/2010 |
| 7797946 | Double U design for mid-turbine frame struts A mid-turbine frame is connected to at least one mount of a gas turbine engine for transferring a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a first load structure, a second load structure, an... | 09/21/2010 |
| 7775050 | Method and apparatus for reducing stresses induced to combustor assemblies A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-... | 08/17/2010 |
| 7775051 | Arrangement for a jet engine combustion chamber The combustion chamber includes a chamber endwall perforated by at least one passage hole. An injection system is mounted so that it can slide diametrically with respect to the passage hole. A deflector is mounted on the chamber endwall. The deflector includes a fit... | 08/17/2010 |
| 7775049 | Integrated strut design for mid-turbine frames with U-base A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load structure and a plurality of struts. The ... | 08/17/2010 |
| 7762086 | Nozzle extension assembly for ground and flight testing An exhaust nozzle for a gas turbine engine according to an exemplary aspect of the present invention includes: an outer cowl; a cowl interface ring attached to the outer cowl; an acoustic nozzle; an acoustic nozzle interface ring attached to the acoustic nozzle, the... | 07/27/2010 |
| 7690207 | Gas turbine floating collar arrangement A crack-resistant floating collar mounting arrangement is provided comprising a collar mounted between spaced-apart mounting flanges, the flange being fixed to a dome from an outer surface unexposed to the hot combustor temperatures. ... | 04/06/2010 |
| 7681403 | Forward sleeve retainer plate and method In a combustor section, having a forward sleeve is disposed to encircle a leading end of an impingement sleeve including first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal j... | 03/23/2010 |
| 7677047 | Inverted stiffened shell panel torque transmission for loaded struts and mid-turbine frames A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a plurality of inverted panels and a plurality of struts. The... | 03/16/2010 |
| 7673460 | System of attaching an injection system to a turbojet combustion chamber base A system of attaching an injection system to a turbojet combustion chamber base. It comprises a deflector welded onto the chamber base. The deflector comprises an annular portion having an edge forming a retaining shoulder directed toward the front of the turbojet a... | 03/09/2010 |
| 7669424 | Combustor assembly A combustor assembly for a gas turbine engine comprises a casing arrangement defining an aperture and a seal element mounted on the casing arrangement through which a component of the combustor can extend. The seal element comprises a relatively flexible force absor... | 03/02/2010 |
| 7661272 | Turbofan jet engine with an ancillary-connecting arm, and the ancillary-connecting arm A turbofan jet engine includes an external easing, connected by radial arms to an annular internal device, downstream of which is mounted, opposite to the external casing, a shell forming a fairing, ancillaries on the outside of the external casing, and ancillaries ... | 02/16/2010 |
| 7640752 | Device for guiding an element in an orifice in a wall of a turbomachine combustion chamber Device for guiding an element in an orifice in a wall of a turbomachine combustion chamber, including a ring and a bush, the ring being traversed axially by the element and including an external annular rim guided transversely in an internal annular channel of the b... | 01/05/2010 |
| 7637110 | Methods and apparatuses for assembling a gas turbine engine A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structur... | 12/29/2009 |
| 7634916 | Stiffener for low pressure compressor for an aircraft engine Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end ... | 12/22/2009 |
| 7617688 | Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber The present invention is concerned with an annular combustion chamber of a gas turbine engine with an external annular wall and an internal annular wall, including an upstream fairing for separating the gas stream at the inlet of the chamber into a combustion stream... | 11/17/2009 |
| 7610763 | Tailorable design configuration topologies for aircraft engine mid-turbine frames A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The mid-turbine frame includes at least one torque box, a first bearing,... | 11/03/2009 |
