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...Daniel Webster invented a "bull plow" to pull out tree stumps. It didn't catch on because it was huge and required four oxen to pull it!
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| Application No. | Application Title | Issue Date |
| 20130086915 | FILM COOLED COMBUSTION LINER ASSEMBLY A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion liner. A seal is attached to the transition piece, and the seal is configur... | 04/11/2013 |
| 20130000310 | FLOW SLEEVE IMPINGEMENT COOLING BAFFLES A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in ... | 01/03/2013 |
| 20120304647 | REVERSE-FLOW ANNULAR COMBUSTOR FOR REDUCED EMISSIONS A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome f... | 12/06/2012 |
| 20120297778 | COMBUSTORS WITH QUENCH INSERTS A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber ther... | 11/29/2012 |
| 20120247120 | APPARATUS AND METHOD FOR COOLING A COMBUSTOR A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for p... | 10/04/2012 |
| 20120198854 | RESONATOR SYSTEM WITH ENHANCED COMBUSTOR LINER COOLING A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and th... | 08/09/2012 |
| 20120144835 | COMBUSTION CHAMBER A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the tiles. Air holes are provided through the wall and the tiles and a flow passage... | 06/14/2012 |
| 20120125006 | GAS TURBINE COMBUSTOR AND GAS TURBINE In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film ... | 05/24/2012 |
| 20120117973 | GAS-TURBINE COMBUSTION CHAMBER WITH A COOLING-AIR SUPPLY DEVICE A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall 6 to be cooled. The cooling-air supply device includes at least one air-supply duct 8 which, in respect of its flow axis, is arranged verti... | 05/17/2012 |
| 20120102960 | GAS TURBINE ENGINE SYSTEMS INVOLVING COOLING OF COMBUSTION SECTION LINERS Gas turbine engine systems involving cooling of combustion section liners are provided. A representative liner includes: an outer side, an inner side, an upstream end, and a downstream end, the outer side being configured to face away from a combustion reaction, the inn... | 05/03/2012 |
| 20120060504 | APPARATUS AND METHOD FOR COOLING A COMBUSTOR A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for p... | 03/15/2012 |
| 20120055165 | COMBUSTOR LINER ASSEMBLY WITH ENHANCED COOLING SYSTEM An enhanced cooling system for the downstream end of a combustor liner assembly is provided. The downstream end region of the combustor liner assembly is formed by a subassembly comprising an outer tubular member, an inner tubular member and a middle band. The middle ba... | 03/08/2012 |
| 20120047909 | COMBUSTOR LINER CONCENTRIC SUPPORT AND METHOD Systems and methods provide for reducing motion which causes wear in a combustor. The method includes attaching a first end of a combustor liner to a retainer which encircles the first end of the combustor liner; attaching the retainer to a combustor casing, where the r... | 03/01/2012 |
| 20110265484 | COMBUSTION DEVICE FOR A GAS TURBINE A combustion device (1) for a gas turbine includes portions (12) having an inner and an outer wall (13, 14) with an interposed noise absorption plate (15) having a plurality of holes (16). The combustion device (1) further has f... | 11/03/2011 |
| 20110214429 | ANGLED VANES IN COMBUSTOR FLOW SLEEVE A turbine combustor liner assembly includes a combustor liner having upstream and downstream ends; a transition duct attached to the downstream end of the combustor liner; a first flow sleeve surrounding the combustor liner, with a first radial flow passage therebetween... | 09/08/2011 |
| 20110185739 | GAS TURBINE COMBUSTORS WITH DUAL WALLED LINERS A combustor for a turbine engine includes a hot wall and a cold wall forming a dual walled liner and a liner cavity with the hot wall. The cold wall defines a plurality of impingement cooling holes configured to deliver an impingement cooling flow. A first downstream en... | 08/04/2011 |
| 20110185740 | COMBUSTOR LINER SEGMENT SEAL MEMBER A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within th... | 08/04/2011 |
| 20110154826 | GAS TURBINE, METHOD OF CONTROLLING AIR SUPPLY AND COMPUTER PROGRAM PRODUCT FOR CONTROLLING AIR SUPPLY The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber casing for accommodating therein a combustor which burns fuel and air compre... | 06/30/2011 |
| 20110107766 | COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE WITH ENHANCED COOLING A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A p... | 05/12/2011 |
| 20110088402 | ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. H... | 04/21/2011 |
| 20110030378 | COMBUSTOR TILE MOUNTING ARRANGEMENT A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use, through the wall of the combustor and has a threaded recess formed therein for ... | 02/10/2011 |
| 20110011093 | GAS-TURBINE COMBUSTION CHAMBER WITH STARTER FILM FOR COOLING THE COMBUSTION CHAMBER WALL A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (5). A base plate (2) is a... | 01/20/2011 |
| 20100307166 | COMBUSTOR-TURBINE SEAL INTERFACE FOR GAS TURBINE ENGINE A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual sea... | 12/09/2010 |
| 20100263384 | COMBUSTOR CAP WITH SHAPED EFFUSION COOLING HOLES A combustor cap assembly for a gas turbine includes a plurality of effusion cooling apertures that allow air to pass through the cooling apertures to cool the combustor cap assembly. An inner diameter of the cooling apertures expands along at least a portion of the tota... | 10/21/2010 |
| 20100257863 | COMBINED CONVECTION/EFFUSION COOLED ONE-PIECE CAN COMBUSTOR An industrial turbine engine comprises a combustion section, an air discharge section downstream of the combustion section, a transition region between the combustion and air discharge section, a combustion transition piece and a sleeve. The transition piece defines an ... | 10/14/2010 |
| 20100251722 | Wall elements for gas turbine engine combustors A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (50A) overlapping a downstream wall element (50B) and defining a gap (37) and an outlet (35) therebetween. In use, a coolant flow exits the outle... | 10/07/2010 |
| 20100186416 | FLOW CONDITIONER FOR USE IN GAS TURBINE COMPONENT IN WHICH COMBUSTION OCCURS A gas turbine component in which combustion occurs. The gas turbine component includes a liner, including a first surface facing a first space and a second surface facing a second space, the liner being interposed between the first and second spaces and having a through... | 07/29/2010 |
| 20100186415 | TURBULATED AFT-END LINER ASSEMBLY AND RELATED COOLING METHOD In a combustor for a turbine a cover sleeve is disposed between the aft end portion of the combustor liner and a resilient seal structure to define an air flow passage therebetween. The cover sleeve has at a forward end thereof a plurality of air inlet feed holes for di... | 07/29/2010 |
| 20100180601 | COOLING STRUCTURE OF GAS TURBINE COMBUSTOR It is required for a gas turbine combustor to exhaust low NOx. The gas turbine combustor is provided with a combustion tube which has a cooling passage through which cooling air flows in a double wall structure. The cooling passage has a main cooling air supply opening ... | 07/22/2010 |
| 20100170259 | METHOD AND APPARATUS TO ENHANCE TRANSITION DUCT COOLING IN A GAS TURBINE ENGINE A method and apparatus are described that include a transition piece including a cooling sleeve. The cooling sleeve includes a first end and an opposite second end, the cooling sleeve is coupled to an inner wall of the transition piece, such that an annular passage is d... | 07/08/2010 |
| 20100170260 | GAS TURBINE COMBUSTOR A gas turbine combustor includes a fuel supplying section and a combustion tube. The fuel supplying section supplies fuel to a combustion zone inside the combustion tube. The combustion tube passes combustion gas to the turbine. The combustion tube is provided with a fi... | 07/08/2010 |
| 20100170258 | COOLING APPARATUS FOR COMBUSTOR TRANSITION PIECE Disclosed is an apparatus for cooling a single-piece duct includes at least one metal wrapper disposed at the transition piece located outboard of the transition piece. At least one support boss is located between the metal wrapper and the transition piece. The support ... | 07/08/2010 |
| 20100126174 | GAS TURBINE COMBUSTION CHAMBER A combustion chamber including: a flame tube having, in the direction of flow, a mixing zone for mixing a fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a post-primary combustion zone, at least one opening being provided in the area o... | 05/27/2010 |
| 20100126184 | COMBUSTION CHAMBER ARRANGEMENT FOR OPERATING A GAS TURBINE A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combus... | 05/27/2010 |
| 20100077764 | Structures with adaptive cooling Disclosed are exemplary structures with adaptive cooling and methods of adaptively cooling structures. A liner is affixed to a support and the liner deflects away from the support when exposed to a localized hot spot in a hot fluid stream. The liner deflection creates a... | 04/01/2010 |
| 20090249791 | TRANSITION PIECE IMPINGEMENT SLEEVE AND METHOD OF ASSEMBLY Disclosed herein is an impingement sleeve for a gas turbine combustion transition piece. The impingement sleeve includes, a housing positionable proximate a first portion of a transition piece body having at least two flanges integrally formed thereon, and a cover posit... | 10/08/2009 |
| 20090193810 | Combustion chamber lining A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profile a... | 08/06/2009 |
| 20090145099 | TRANSITION DUCT COOLING FEED TUBES Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleev... | 06/11/2009 |
| 20090145132 | METHODS AND SYSTEM FOR REDUCING PRESSURE LOSSES IN GAS TURBINE ENGINES A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an... | 06/11/2009 |
| 20090120096 | Gas Turbine Engine Systems Involving Cooling of Combustion Section Liners Gas turbine engine systems involving cooling of combustion section liners are provided. In this regard, a representative liner includes: an outer side, an inner side, an upstream end and a downstream end, the outer side being configured to face away from a combustion re... | 05/14/2009 |
