-
公开(公告)号：US20210147061A1
公开(公告)日：2021-05-20
申请号：US16685527
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Brian Magann Rush , Narendra Digamber Joshi , Timothy John Sommerer , Gregory Alexander Natsui , Brian Gene Brzek , Douglas Carl Hofer
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.
-
公开(公告)号：US20210140641A1
公开(公告)日：2021-05-13
申请号：US16682122
申请日：2019-11-13
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi
Abstract: A rotating detonation combustion (RDC) assembly and propulsion system, and method for operation, are provided. The RDC assembly includes a detonation path extended from a detonation zone at which a predetonation device is in operative communication with a fuel/oxidizer mixture at a detonation chamber. The method includes generating a first fuel/oxidizer equivalence ratio of detonation gases at a first portion of the detonation path, wherein the first portion of the detonation path is defined along a first direction from the detonation zone along which a detonation wave propagates; generating a second fuel/oxidizer equivalence ratio of detonation gases at the second portion of the detonation path, wherein the second fuel/oxidizer equivalence ratio is different from the first fuel/oxidizer equivalence ratio, and wherein the second portion of the detonation path is defined from the first portion to the predetonation device; and sustaining the detonation wave via the second fuel/oxidizer equivalence ratio of detonation gases at the second portion of the detonation path.
-
公开(公告)号：US10969107B2
公开(公告)日：2021-04-06
申请号：US15705954
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Owen James Sullivan Rickey , Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Shashank Yellapantula
Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.
-
公开(公告)号：US20210010376A1
公开(公告)日：2021-01-14
申请号：US17034147
申请日：2020-09-28
Applicant: General Electric Company
Inventor： Daniel Jason Erno , Narendra Digamber Joshi , William Dwight Gerstler
Abstract: A heat exchanger includes an airfoil configured to be positioned in a coolant stream. The airfoil includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge. The leading edge defines an impingement zone wherein the coolant stream is configured to impinge the airfoil. The heat exchanger also includes at least one channel defined within the airfoil between the pressure sidewall and the suction sidewall. The at least one channel is at least partially defined within the impingement zone proximate the leading edge.
-
公开(公告)号：US10830056B2
公开(公告)日：2020-11-10
申请号：US15424021
申请日：2017-02-03
Applicant: General Electric Company
Inventor： Daniel Jason Erno , Narendra Digamber Joshi , William Dwight Gerstler
Abstract: A heat exchanger includes an airfoil configured to be positioned in a coolant stream. The airfoil includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge. The leading edge defines an impingement zone wherein the coolant stream is configured to impinge the airfoil. The heat exchanger also includes at least one channel defined within the airfoil between the pressure sidewall and the suction sidewall. The at least one channel is at least partially defined within the impingement zone proximate the leading edge.
-
Patent Agency Ranking
公开(公告)号：US10823126B2
公开(公告)日：2020-11-03
申请号：US16118895
申请日：2018-08-31
Applicant: General Electric Company
Abstract: A flow control actuator includes at least one side wall, an upstream wall coupled to an upstream end of the side wall, a downstream cap coupled to a downstream end of the side wall, the downstream cap comprising at least one orifice disposed therein, at least one fuel injector disposed in at least one of the upstream wall, and the sidewall, the fuel injector dispersing fuel into the interior of the flow control actuator, and at least one oxidizer inlet disposed in at least one of the upstream wall and the sidewall, the at least one oxidizer inlet introducing an oxidizer into the interior of the flow control actuator. The flow control actuator includes at least one external fuel injector disposed adjacent to the side wall. The fuel from the fuel injector and oxidizer from the oxidizer inlet ignite in the interior of the flow control actuator.
-
公开(公告)号：US10712002B2
公开(公告)日：2020-07-14
申请号：US14801962
申请日：2015-07-17
Applicant: General Electric Company
Inventor： Matthieu Marc Masquelet , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Sarah Marie Monahan
Abstract: A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.
-
公开(公告)号：US20200166212A1
公开(公告)日：2020-05-28
申请号：US16203335
申请日：2018-11-28
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi
Abstract: A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one annulus inlet disposed in the annular tube proximate the inlet end, the annulus inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one inlet fluid plenum disposed upstream of the annulus inlet; and at least one fluid inlet disposed upstream of the inlet fluid plenum. The fluid inlet is linearly offset from the annulus inlet.
-
公开(公告)号：US20200149743A1
公开(公告)日：2020-05-14
申请号：US16185208
申请日：2018-11-09
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi , Thomas Michael Lavertu , Thomas Earl Dyson , Andrew Thomas Cross
Abstract: A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one fluid inlet disposed in the annular tube proximate the inlet end, the fluid inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; and at least one cooling feature disposed at an underside of the inner wall or the outer wall. The cooling feature maintains a temperature of the inner wall or the outer wall within a predetermined range.
-
公开(公告)号：US10590849B2
公开(公告)日：2020-03-17
申请号：US14663871
申请日：2015-03-20
Applicant: General Electric Company
Inventor： Ross Hartley Kenyon , Narendra Digamber Joshi
IPC: F02C1/00 , F02C7/14 , F02C7/16 , F02C9/18 , F02C7/143 , F02C3/30 , F02C6/00 , F02K3/11 , F02K3/075 , F02K7/14 , F02K3/10 , F01D13/02 , F01D13/00 , F01D25/12
Abstract: A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.
-
-
-
-
-
-
-
-
-
Search Results
134
records
(took 0.021 seconds)
