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7617684 |
Impingement cooled can combustor
A can combustor includes a generally cylindrical housing having an interior, an axis, and a closed axial end. The closed axial end includes means for introducing fuel to the housing interior. A...
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7588413 |
Upstream plasma shielded film cooling
An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of...
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7571611 |
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...
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7096668 |
Cooling and sealing design for a gas turbine combustion system
An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are...
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7089748 |
Combustion chamber, in particular of a gas turbine
The invention relates to a combustion chamber, in particular of a gas turbine, comprising an external wall structure that surrounds an internal area and an internal wall, which is formed by the...
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7051532 |
Methods and apparatus for film cooling gas turbine engine combustors
A method facilitates assembling a combustor for a gas turbine engine. The method includes providing a dome assembly that includes at least one cooling slot lip and at least one filler projection,...
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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...
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7032386 |
Gas turbine combustor
A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle...
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7007481 |
Thick coated combustor liner
A combustor liner includes panels joined together at a cooling nugget including a bridge and a lip extending therefrom. The lip defines a slot terminating in an outlet. Thermal barrier coating...
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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...
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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...
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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...
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6890148 |
Transition duct cooling system
Aspects of the present invention relate to hollow elongated turbine engine components, such as transition ducts, having a cooling system. The component can have first and second ends, and can be...
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6886341 |
Gas-turbine engine combustor
A gas-turbine engine combustor having a plurality of venturi mixers, each connected to an air supply path that passes air compressed by a compressor and to a supply source of gaseous fuel, which...
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6840049 |
Gas turbine and method for operating a gas turbine
The invention relates to a gas turbine ( 3 ) with reheat in the turbine section ( 11 ), whereby a fuel injection device ( 37 ) is provided for the injection of fuel ( 33 ) in to a combustion air...
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6837053 |
Gas turbine combustion chamber and air guidance method therefore
In order to provide a method of air guidance and a design for a gas turbine combustion chamber which permits improved cooling and reduced pressure losses and which avoids the overcooling phenomena...
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6810672 |
Gas turbine combustor, particularly for an aircraft engine
A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for...
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6761031 |
Double wall combustor liner segment with enhanced cooling
A connector segment for connecting a combustor liner and a transition piece in a gas turbine has a substantially cylindrical shape and is of double-walled construction including inner and outer...
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6732528 |
Gas turbine combustor
An internal cylinder which has the opening section from which combustion gas is blown out is inserted into the tail cylinder which becomes a flow path of the combustion gas, and is engaged with the...
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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...
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6705832 |
Turbine
A turbine includes a sealing element with a receiving area for sealing the guide blade vanes which are adjacent to each other in the peripheral direction of the turbine. The foot plates of the...
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6702549 |
Turbine installation
A turbine installation, especially a gas turbine installation, includes foot plates of the guide blades of adjacent turbine stages being interconnected with a clip-type sealing element on their...
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6675582 |
Slot cooled combustor line
A combustor liner for use in a gas turbine engine includes an annular panel section having a cooling nugget formed on one end thereof. An annular cooling lip is formed on the cooling nugget so as...
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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...
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6651437 |
Combustor liner and method for making thereof
A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially...
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6640547 |
Effusion cooled transition duct with shaped cooling holes
An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a...
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6568187 |
Effusion cooled transition duct
An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a...
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6553766 |
Cooling structure of a combustor tail tube
A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the...
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6546731 |
Combustion chamber for a gas turbine engine
In a twin wall combustion chamber for a gas turbine engine, the outer wall has impingement holes so that compressed air surrounding the chamber can pass through the holes to impinge on the inner...
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6543233 |
Slot cooled combustor liner
A combustor liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second...
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6536201 |
Combustor turbine successive dual cooling
The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and...
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6494044 |
Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
A transition piece assembly for a gas turbine includes a transition duct having one end adapted for connection to a gas turbine combustor and an opposite end adapted for connection to a first...
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6434821 |
Method of making a combustion chamber liner
A method of fabricating an annular liner for a combustion chamber of a gas turbine engine. The combustion chamber has a dome including a fuel nozzle for delivering fuel to the combustion chamber. A...
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6427446 |
Low NOx emission combustion liner with circumferentially angled film cooling holes
An improved dual-stage, dual-mode turbine combustor capable of reducing nitric oxide (NOx) emissions is disclosed. This can-annular combustor utilizes multiple, single wall sheet metal combustor...
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6408628 |
Wall elements for gas turbine engine combustors
A wall element ( 29 A, 29 B) for a combustor ( 20 ) of a gas turbine engine ( 10 ). The wall element ( 29 A, 29 B) defines an axis. In use, the axis is arranged generally parallel to the...
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6286317 |
Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity
A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and...
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6282905 |
Gas turbine combustor cooling structure
Cooling structure of gas turbine combustor in which cooling medium flows through grooves in wall is improved so that adjustment of flow velocity, pressure loss and heat transfer rate of cooling...
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6220036 |
Cooling structure for combustor tail pipes
Gas turbine combustor tail tube cooling structure is improved so that temperature distribution along tail tube axial direction is made gentle and large thermal stress is prevented from occurring...
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6173561 |
Steam cooling method for gas turbine combustor and apparatus therefor
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6164075 |
Steam cooling type gas turbine combustor
This invention concerns the use of pressurized steam as the cooling medium in the combustor wall of a gas turbine combustor. It is distinguished by the following. The combustor wall is configured...
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6105371 |
Control of cooling flows for high-temperature combustion chambers having increased permeability in the downstream direction
The invention relates to the control of air flows for cooling the axial walls of a high-temperature combustion chamber in which the walls are provided with through holes forming multiple...
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6101814 |
Low emissions can combustor with dilution hole arrangement for a turbine engine
A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays of dilution holes 52, 54, 56. The first hole array comprises twelve...
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6085515 |
Heat shield configuration, particularly for structural parts of gas turbine plants
A heat shield configuration, particularly for protecting supporting structures and structural parts of gas turbine plants against a hot fluid. The heat shield has an inner lining which consists of...
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6079199 |
Double pass air impingement and air film cooling for gas turbine combustor walls
A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of...
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6029455 |
Turbojet engine combustion chamber with heat protecting lining
A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The...
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6018950 |
Combustion turbine modular cooling panel
A modular cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper...
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5775108 |
Combustion chamber having a multi-hole cooling system with variably oriented holes
A combustion chamber, particularly for a turbomachine, has at least one generally axially extending wall provided with a plurality of through holes defining a multi-hole cooling system for the...
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5755093 |
Forced air cooled gas turbine exhaust liner
The exhaust in a gas turbine engine is lined with stacks of hollow cooling blocks made of a composite material. Air is pumped into each stack and escapes into the exhaust flow from a slot between...
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5749229 |
Thermal spreading combustor liner
A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than...
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5746048 |
Combustor for a gas turbine engine
A compact gas turbine engine having improved fuel efficiency, lower emissions, better starting capability, and longer operational life is provided at low cost through the use of a combustor...
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