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公开(公告)号：US20240053017A1
公开(公告)日：2024-02-15
申请号：US18122067
申请日：2023-03-15
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： F23R3/52 , F02C7/143 , F02C3/04 , F02C7/10 , F02C6/12 , F23R3/32 , F02K1/00 , F02K1/36 , F02K3/10 , F23R3/00
CPC分类号： F23R3/52 , F02C7/143 , F02C3/04 , F02C7/10 , F02C6/12 , F23R3/32 , F02K1/002 , F02K1/36 , F02K3/10 , F23R3/007 , F23R3/002 , F05D2220/32 , F05D2260/211 , F05D2300/6033 , F05D2260/4023 , Y02T50/60
摘要： A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.
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公开(公告)号：US11635211B2
公开(公告)日：2023-04-25
申请号：US16255632
申请日：2019-01-23
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： F23R3/52 , F23R3/00 , F02C7/143 , F02C3/04 , F02C7/10 , F02C6/12 , F23R3/32 , F02K1/00 , F02K1/36 , F02K3/10
摘要： A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.
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公开(公告)号：US20220333530A1
公开(公告)日：2022-10-20
申请号：US17231487
申请日：2021-04-15
摘要： A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.
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公开(公告)号：US20200300166A1
公开(公告)日：2020-09-24
申请号：US16656529
申请日：2019-10-17
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： F02C7/143 , F02C3/04 , F02C7/10 , F02C6/12 , F23R3/32 , F02K1/00 , F02K1/36 , F02K3/10 , F23R3/00 , F23R3/52
摘要： A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.
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公开(公告)号：US10704469B2
公开(公告)日：2020-07-07
申请号：US15643736
申请日：2017-07-07
申请人： Woodward, Inc.
发明人： Bidhan Dam , Jimroy McCormack , Fei Philip Lee , Conor Riordan , Logan Oonk , Erik Pederson , Michael Stratton
IPC分类号： F02C7/264 , F02C7/266 , F23R3/34 , F23R3/28 , F02C7/22 , F02C7/18 , F23R3/14 , F23R3/32 , F23R3/04
摘要： A torch igniter includes an auxiliary fuel injector; an ignition source; and an igniter body carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber having a side wall extending axially from a first end wall to a second end wall, the side wall defining an interior cavity between the first and second end walls. The igniter body further includes a premixing cup residing within the interior cavity including a cylindrical wall radially surrounding the auxiliary fuel injector and an auxiliary air inlet, the cylindrical wall of the premixing cup protruding axially outward relative to the first end wall of the auxiliary combustion chamber through a portion of the interior cavity to delineate a premixing zone radially inward of the cylindrical wall and a recirculation zone radially outward of the cylindrical wall.
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公开(公告)号：US10571126B2
公开(公告)日：2020-02-25
申请号：US15427831
申请日：2017-02-08
IPC分类号： F23R3/32 , F23R3/28 , B01F13/00 , B23K1/00 , B23K1/19 , F23D14/64 , F23R3/04 , B23K101/00 , B23K103/04
摘要： Manufactured articles, and methods of manufacturing enhanced wear protected components and articles. More particularly, wear protected components and articles, such as combustor components of turbine engines, and even more particularly enhanced wear protected micromixer tubes and assemblies thereof with one or more micromixer plates, the micromixer tubes having wear protection for enhanced performance and reduced wear related failure. Methods including surface treatment to enhance wear, including vacuum braze application of coatings to enhance surface hardness for wear benefits.
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公开(公告)号：US20190153948A1
公开(公告)日：2019-05-23
申请号：US16255632
申请日：2019-01-23
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： F02C7/143 , F23R3/52 , F02C7/10 , F02K1/00 , F02K1/36 , F02K3/10 , F02C3/04 , F23R3/32 , F02C6/12 , F23R3/00
摘要： A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.
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公开(公告)号：US10094567B2
公开(公告)日：2018-10-09
申请号：US14461532
申请日：2014-08-18
发明人： Shota Igarashi , Hirokazu Takahashi
摘要： A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve.
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公开(公告)号：US20170356657A1
公开(公告)日：2017-12-14
申请号：US15603396
申请日：2017-05-23
发明人： Timothy C Roesler
摘要： A gas turbine engine and a combustor are described herein. The combustor includes a fuel vaporizer coupled to a combustor wall, which extends into a combustion chamber. A fuel injector having a nozzle extends within a portion of the fuel vaporizer. A dome swirler is coupled to an upstream dome portion of the combustor wall. The swirler surrounds a heat shield, which may have a concaved body. The outlet end of the fuel vaporizer is disposed over the heat shield, which may be over the central zone of the heat shield, to face the heat shield. The fuel vaporizer may be coupled to the combustor wall and disposed outside the swirler. Fuel and air mixture exits the vaporizer and impinges against the heat shield and is then combined with the swirler air to become part of the primary zone recirculation.
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公开(公告)号：US09599343B2
公开(公告)日：2017-03-21
申请号：US13687071
申请日：2012-11-28
CPC分类号： F23R3/286 , F23D11/402 , F23D14/62 , F23D14/64 , F23R3/32 , Y10T29/49229
摘要： A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes at least one premixer tube including a tube wall and a plurality of perforations defined therein and extending through the tube wall. The plurality of perforations are configured to channel a flow of air therethrough. The fuel nozzle also includes a liquid fuel plenum positioned upstream from the premixer tube, and at least one fuel injector coupled in flow communication with the liquid fuel plenum and the at least one premixer tube. The at least one fuel injector is configured to channel a flow of liquid fuel from the liquid fuel plenum into the premixer tube.
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