Did You Know...
...that two musicians were responsible for the invention of color print film? Fascinated by photography, Leopold Godowsky and Leopold Mannes worked together to produce an easy-to-use, practical color film. They worked full time as music teachers and gave concerts while experimenting during their off hours in Mannes' kitchen. Their success earned them full-time, well-paying jobs at Kodak and their efforts resulted in Kodachrome film, which was introduced in 1935.
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 |
| 8104288 | Effusion cooling techniques for combustors in engine assemblies A combustor for an engine assembly includes a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such... | 01/31/2012 |
| 8051663 | 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 combustio... | 11/08/2011 |
| 8024933 | Wall elements for gas turbine engine combustors The invention relates to a wall element for a wall structure of a gas turbine engine combustor. The wall element has an inner, in use, hot surface, and an outer, in use, cooler surface. A plurality of projections is provided on the outer surface to facilitate heat t... | 09/27/2011 |
| 8015818 | Cooled transition duct for a gas turbine engine A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40) disposed remote from the bent corner regions ... | 09/13/2011 |
| 7886541 | 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 o... | 02/15/2011 |
| 7712314 | Venturi cooling system A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines a ... | 05/11/2010 |
| 7707836 | Venturi cooling system A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines an... | 05/04/2010 |
| 7441409 | Combustor liner v-band design A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combusto... | 10/28/2008 |
| 7363763 | Combustor A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a ... | 04/29/2008 |
| 7299634 | Combustion chamber A combustion chamber (4) for a gas turbine (1), the combustion chamber wall (24) of which is furnished on the inside with a lining formed of a number of heat shield elements (26), is to be designed for a particularly high level of operati... | 11/27/2007 |
| 7216485 | Adjusting airflow in turbine component by depositing overlay metallic coating A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes ar... | 05/15/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7146815 | Combustor A combustor heat shield panel is secured relative to a combustor shell so as to hold the panel exterior surface spaced apart from and facing the shell interior surface over major area of the panel exterior surface. A gap is formed between the heat shield exterior su... | 12/12/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7097448 | Vortex type gas lamp A vortex type gas lamp comprising a base and an axially extending-transparent shield. Gas is supplied near the bottom end of the shield. The shield is formed of a plurality (preferably two) axial curved sections which overlap one another at their axial edges to form... | 08/29/2006 |
| 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 |
| 7089742 | Wall elements for gas turbine engine combustors A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality... | 08/15/2006 |
| 7082766 | One-piece can combustor A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless. ... | 08/01/2006 |
| 7082771 | Combustion chamber A combustion chamber (4) of a gas turbine (1), the combustion space (24) of which is bounded by an annular combustion chamber inner wall (28) and a combustion chamber outer wall (26), in which in order to generate a working medium ... | 08/01/2006 |
| 7080515 | Gas turbine can annular combustor A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly ... | 07/25/2006 |
| 7051531 | Flow control body In order to develop a flow control body (6) for separate control of a cooling fluid inflow and a cooling fluid outflow for combustion chambers with a closed cooling system for turbines such that a simplified cooling fluid flow control is made possible in the ... | 05/30/2006 |
| 7036316 | Methods and apparatus for cooling turbine engine combustor exit temperatures A method facilitates assembling a combustor for a gas turbine engine. The method comprises coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, positioning an outer support a distance radially outward from the outer liner... | 05/02/2006 |
| 7010921 | Method and apparatus for cooling combustor liner and transition piece of a gas turbine A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an... | 03/14/2006 |
| 6973419 | Method and system for designing an impingement film floatwall panel system A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of d... | 12/06/2005 |
| 6968672 | Collar for a combustion chamber of a gas turbine engine This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connec... | 11/29/2005 |
| 6957538 | Combustion chamber for a gas turbine The invention relates to a combustion chamber for a gas turbine having at least one closed-circuit-cooled burner insert which can be disposed in an inlet opening of the combustion chamber for the purpose of feeding and/or igniting a combustible gas/air mixture, and ... | 10/25/2005 |
| 6912782 | Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 07/05/2005 |
| 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 |
| 6908657 | Coated component with through-hole having improved surface finish A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of... | 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 |
| 6871501 | Method and apparatus to decrease gas turbine engine combustor emissions A method enables a gas turbine engine including a combustor to be operated. The combustor includes a mixer assembly including an air swirler, a premixer, a dome plate, and a heat shield. The method comprises discharging fluids from the air swirler into the premixer,... | 03/29/2005 |
| 6860108 | Gas turbine tail tube seal and gas turbine using the same In order to provide a gas turbine tail tube seal which can prevent an outer shroud and an inner shroud in a first row stationary blade from being damaged by heat and from being worn, and to provide a gas turbine having the above-mentioned gas turbine tail tube seal,... | 03/01/2005 |
| 6851263 | Liner for a gas turbine engine combustor having trapped vortex cavity A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner p... | 02/08/2005 |
| 6761033 | Gas turbine combustor with fuel-air pre-mixer and pre-mixing method for low NOx combustion The purpose is to improve the mixture ratio of a pre-mixer by a simple arrangement to form a more uniform premixed gases so as to materialize low NOx combustion. Two fuel nozzles disposed circumferentially of a pre-mixer are combined with a single air intake window ... | 07/13/2004 |
| 6725666 | Combustion-chamber arrangement The invention relates to a combustion-chamber arrangement for gas turbines, having an annular combustion chamber connected to at least one burner and leading into a turbine space, an annular-combustion-chamber wall which defines the annular combustion chamber being ... | 04/27/2004 |
| 6711900 | Combustor liner V-band design A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combusto... | 03/30/2004 |
| 6679063 | Combustion chamber head for a gas turbine The present invention relates to a combustion chamber head for a gas turbine with at least one combustion chamber wall 2,3, a metering panel 1, at least one heat shield 4, at least one sleeve 5 and a cowling 6, characterized in that the metering panel 1 f... | 01/20/2004 |
| 6675586 | Heat shield arrangement for a component carrying hot gas, in particular for structural parts of gas turbines In a heat shield arrangement, in which heat shield elements are arranged next to one another on a carrying structure and are anchored to the carrying structure, there is provision for a cooling-air duct, into which cooling air is fed and which the adjacen... | 01/13/2004 |
| 6655146 | Hybrid film cooled combustor liner A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located... | 12/02/2003 |
| 6609362 | Apparatus for adjusting combustor cycle A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is ... | 08/26/2003 |
