-
公开(公告)号：US12104795B2
公开(公告)日：2024-10-01
申请号：US17664975
申请日：2022-05-25
摘要： A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.
-
公开(公告)号：US12053821B2
公开(公告)日：2024-08-06
申请号：US18122207
申请日：2023-03-16
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
-
公开(公告)号：US11846422B2
公开(公告)日：2023-12-19
申请号：US17406767
申请日：2021-08-19
申请人： Delavan Inc.
IPC分类号： F23R3/28 , F02C7/18 , F02C7/224 , F02C9/18 , F23R3/26 , F02C6/08 , F02C7/141 , F02C7/22 , F02C9/16
CPC分类号： F23R3/283 , F02C7/185 , F02C7/224 , F02C9/18 , F23R3/26 , F02C6/08 , F02C7/141 , F02C7/222 , F02C9/16 , F05D2260/213 , F05D2260/232 , F05D2270/303
摘要： A system includes an air manifold, a fuel manifold, and a plurality of fuel injectors. At least one of the fuel injectors includes a heat exchanger portion for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.
-
公开(公告)号：US11725822B2
公开(公告)日：2023-08-15
申请号：US16423953
申请日：2019-05-28
发明人： Romain Nicolas Lunel , Damien Bonnefoi , Christophe Pieussergues , Luc Namer , Dominique Raulin , Dan Ranjiv Joory , Benjamin Frantz Karl Villenave
CPC分类号： F23R3/60 , F02C3/06 , F02C7/20 , F02C7/22 , F02C9/16 , F23R3/26 , F23R3/28 , F05D2220/323 , F05D2260/30
摘要： The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).
-
公开(公告)号：US20230241681A1
公开(公告)日：2023-08-03
申请号：US18122207
申请日：2023-03-16
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
-
公开(公告)号：US11578669B2
公开(公告)日：2023-02-14
申请号：US17412698
申请日：2021-08-26
发明人： Ninad Joshi , Sid-Ali Meslioui
摘要： A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.
-
公开(公告)号：US11499480B2
公开(公告)日：2022-11-15
申请号：US16940953
申请日：2020-07-28
摘要： A combustor cap assembly, combustor and related method are disclosed. The combustor cap assembly includes: an impingement plate defining a plurality of impingement cooling holes with a first side of the impingement plate in fluid communication with a cooling air plenum. The assembly also includes a combustor cap plate coupled to the impingement plate, such that an impingement air plenum is defined between a second side of the impingement plate and the combustor cap plate. Tubes extend from at least a portion of the plurality of impingement cooling holes at the second side of the impingement plate and extend partially towards the combustor cap plate through the impingement air plenum. The plurality of impingement cooling holes provides for fluid communication between the cooling air plenum and the impingement air plenum through the tubes.
-
公开(公告)号：US11421881B2
公开(公告)日：2022-08-23
申请号：US17405500
申请日：2021-08-18
摘要： An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.
-
公开(公告)号：US11421880B2
公开(公告)日：2022-08-23
申请号：US17402075
申请日：2021-08-13
摘要： An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.
-
公开(公告)号：US11293292B2
公开(公告)日：2022-04-05
申请号：US16736199
申请日：2020-01-07
发明人： Jason Smoke , David K. Jan , Mark Matwey
摘要： A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
-
-
-
-
-
-
-
-
-
搜索结果
596 条记录 (耗时 0.023 秒)
