Celebrity Inventors
Mark Twain (Samuel L. Clemens) received Patent No. 121,992 for "An Improvement in Adjustable and Detachable Straps for Garments." He later received two more patents: one for a self-pasting scrapbook and one for a game to help players remember important historical dates.
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| Number | Title | Issue Date |
| 8011188 | Augmentor with trapped vortex cavity pilot A gas turbine engine augmentor includes an annular trapped vortex cavity pilot having a cavity forward wall, a cavity radially outer wall, and a cavity aft wall, an annular cavity therebetween, and cavity fuel injector tubes operably disposed through the outer wall ... | 09/06/2011 |
| 7966823 | Exhaust dust flow splitter system A gas turbine engine augmentor includes an augmentor outer casing 502 and an annular augmentor liner 504 disposed radially within and radially separated from the augmentor outer casing 502 to form a generally annular augmentor liner cooling flow... | 06/28/2011 |
| 7870740 | Turbojet engine comprising an afterburner duct cooled by a variable-throughput ventilation stream An afterbody for a turbojet engine is disclosed. The afterbody includes an afterburner casing, a thermal protection liner, and a diaphragm-forming assembly interposed between the liner and the casing. The diaphragm-forming assembly defines a flow area which is trave... | 01/18/2011 |
| 7614236 | Positioning bridge guide and its utilisation for the nozzle support pipe of a turboprop A bridge positioned between two parts, such as a nozzle support pipe envelope and a heat shield liner, includes a central part with inversed curvature thus having two contact zones with the nozzle support pipe envelope. Furthermore, the bridge includes two lugs, one... | 11/10/2009 |
| 7437876 | Augmenter swirler pilot A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a s... | 10/21/2008 |
| 7401682 | Architecture for an acoustic liner An acoustic liner 20 includes a remote panel 26, a perforated proximate panel 22 transversely spaced from the remote panel and one or more partitions 32 spanning across the space between the panels. At least one baffle 44 cooperate... | 07/22/2008 |
| 7350619 | Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a bulkhead collar on the aircraft, a body section that is coupled to the... | 04/01/2008 |
| 7334409 | Retractable afterburner for jet engine The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable... | 02/26/2008 |
| 7311175 | Acoustic liner with bypass cooling An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in regist... | 12/25/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7251941 | Ablative afterburner An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust. ... | 08/07/2007 |
| 7225623 | Trapped vortex cavity afterburner A trapped vortex cavity afterburner includes one or more trapped vortex cavity stages for injecting a fuel/air mixture into a combustion zone. The trapped vortex cavity afterburner is operable to provide all thrust augmenting fuel used for engine thrust augmentation... | 06/05/2007 |
| 7168253 | Monobloc flameholder arm for an afterburner device of a bypass turbojet A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together ... | 01/30/2007 |
| 7114321 | Thermal isolation device for liquid fuel components A thermal isolation device for a gas turbine combustor assembly includes a plurality of substantially flat plates secured in spaced relationship by a plurality of columns, at least one column incorporating a bolt hole for use in securing the device between a pair of... | 10/03/2006 |
| 7093442 | Augmentor A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has ... | 08/22/2006 |
| 7093439 | Heat shield panels for use in a combustor for a gas turbine engine The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plu... | 08/22/2006 |
| 7013551 | Method or manufacturing thin wall isogrid casings In one aspect of the invention a method of manufacturing a thin wall isogrid casing by a chip machining process comprises the steps of: positioning a substantially cylindrical casing (10) on a support (20); the support having a substantially continuous... | 03/21/2006 |
| 6907736 | Gas turbine combustor having an acoustic energy absorbing wall A gas turbine combustor in which a part or all of the wall of the combustor disposed within an intake chamber is formed as an acoustic energy absorbing member that can absorb the acoustic energy of a combustion variation generated within the combustor. The acoustic ... | 06/21/2005 |
| 6901757 | Heat shield arrangement with sealing element A heat shield arrangement includes several tiles 1 and several fasteners 6 for attaching the tiles at a spaced distance to a wall 2 to form an interspace 4 between the wall and the tiles which can be supplied with cooling air. At least on... | 06/07/2005 |
| 6792748 | Cooling system for a gas turbine engine post-combustion jet nozzle The invention concerns a cooling system for a post combustion jet nozzle, The jet nozzle includes a primary gas duct allowing a primary flow of gas, and a secondary air duct allowing a secondary flow of air. The secondary air duct surrounds the primary gas duct and ... | 09/21/2004 |
| 6782693 | Case burning rocket with drive system for combustion chamber and nozzle A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case a... | 08/31/2004 |
| 6701714 | Gas turbine combustor A combustor for a gas turbine engine is provided which includes a plurality of liner segments and a support shell. The support shell includes an interior and an exterior surface, a plurality of mounting holes, and a plurality of impingement coolant holes ... | 03/09/2004 |
| 6694723 | Valve assembly for gas turbine engine A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve as... | 02/24/2004 |
| 6418709 | Gas turbine engine liner A liner for a gas turbine engine is provided that includes a first liner section and a second liner section. The first liner section includes a first flange having a first contact surface. The second liner section includes a second flange having a second ... | 07/16/2002 |
| 6199371 | Thermally compliant liner The present invention relates to a thermally compliant liner for a gas turbine engine. The liner includes an outer wall, an inner wall spaced radially inwardly from the outer wall leaving a duct therebetween. A plurality of stiffeners are disposed in the ... | 03/13/2001 |
| 6041590 | Jet pipe liner A jet pipe liner for a gas turbine engine comprises of an inner skin consisting of a multiplicity of longitudinally extending sections arranged edge-to-edge in a circumferential direction and suspended along their edges by a multiplicity of longitudinally... | 03/28/2000 |
| 5778658 | Recoup turbojet engine A turbojet engine includes a compressor and turbine, with a combustor disposed therebetween for generating exhaust gas. An afterburner includes an annular casing and liner spaced radially inwardly therefrom to define a cooling duct therebetween. A recoup ... | 07/14/1998 |
| 5775589 | Cooling apparatus for aircraft gas turbine engine exhaust nozzles The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream fl... | 07/07/1998 |
| 5704208 | Serviceable liner for gas turbine engine A serviceable liner is provided comprising an outer wall, an inner wall, a plurality of standoffs disposed between the walls, and a plurality of attachment assemblies for attaching the walls to one another. The outer wall includes a plurality of first ape... | 01/06/1998 |
| 5697213 | Serviceable liner for gas turbine engine A liner for a gas turbine engine is provided which includes an outer wall, an inner wall, a plurality of standoffs, a plurality of attachment assemblies, and a plurality of tapered ribs. The inner wall sections each have a first edge and a second edge. Th... | 12/16/1997 |
| 5690279 | Thermal relief slot in sheet metal A thermal relief slot is formed by including a lateral slot in each of three overlying sheet metal sheets with the upper and lower slots being in overlying position and the middle slot being axially spaced therefrom and the three sheets being bonded into ... | 11/25/1997 |
| 5560198 | Cooled gas turbine engine augmentor fingerseal assembly An augmentor for a gas turbine engine with a nozzle is provided having an outer casing, a liner, a stiffening ring, a plurality of fingerseals, and apparatus for fastening the stiffening ring and the fingerseals to the liner. The liner includes a pluralit... | 10/01/1996 |
| 5483794 | Multi-hole film cooled afterburner combustor liner The present invention provides a cooling apparatus with two spaced apart walls, one of which is a coolable wall, having a cooling flowpath between them wherein the cooling flowpath is converging in the direction of the cooling flow. In one embodiment the ... | 01/16/1996 |
| 5367874 | Integral composite gas turbine afterburner structure An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body... | 11/29/1994 |
| 5269137 | Gas turbine elements bearing coke inhibiting coatings of alumina Fuel contacting elements for gas turbines comprise high temperature alloys having a coke inhibiting layer of alumina thereupon.... | 12/14/1993 |
| 5249419 | Nozzle liner for gas turbine engines The improved liner comprises a base plate that mounts to the wall of the nozzle, at least one inner tube having a plurality of leg supports thereon for mounting to the base plate, a cylindrical seal attached to the bottom of the inner tube, and an outer t... | 10/05/1993 |
| 5233828 | Combustor liner with circumferentially angled film cooling holes A gas turbine engine combustor is provided, having a an annular single wall sheet metal liner which is generally annular in shape and having disposed therethrough a multi-hole film cooling means which includes at least one pattern of small closely spaced ... | 08/10/1993 |
| 5230214 | Recirculating zone inducing means for an augmentor burning section Juxtaposed recirculation zones for the pilot in the burner of an augmentor for a gas turbine engine is created by fabricating the engine's tail cone in two components and including an annular gap defined between the juncture of both components that inject... | 07/27/1993 |
| 5209059 | Active cooling apparatus for afterburners The present invention comprises at least one active cooling apparatus incorporated into the nozzle liner of sidewall of an afterburner. The liner has a plurality of cooling air holes located under the apparatus. Within the liner is a supply of cooling air... | 05/11/1993 |
| 5201887 | Damper for augmentor liners Damping of the leading edge of a cantilevered mounted liner for the augmentor of a gas turbine engine is obtained by incorporating a generally annular shaped member having a U-shaped cross section and encapsulating the leading edge of the liner in the U-s... | 04/13/1993 |
