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公开(公告)号：US10415833B2
公开(公告)日：2019-09-17
申请号：US15434830
申请日：2017-02-16
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Jin Yan , Anthony John Dean
Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
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公开(公告)号：US20180180289A1
公开(公告)日：2018-06-28
申请号：US15390052
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Thomas Michael Lavertu, Jr. , Andrew Maxwell Peter , Venkat Eswarlu Tangirala , James Albert Tallman , Anthony John Dean
IPC: F23R7/00
CPC classification number: F23R7/00 , F23R3/56 , F23R2900/03041
Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.
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公开(公告)号：US20170102147A1
公开(公告)日：2017-04-13
申请号：US14879793
申请日：2015-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Liangyu Wang , Anthony John Dean , Keith Robert McManus , Kapil Kumar Singh , Suhui Li , Sravan Kumar Dheeraj Kapilavai , Mathew Paul Thariyan , Owen Graham
CPC classification number: F23R3/14 , F02C3/04 , F02C7/222 , F05D2220/32 , F05D2260/14 , F23C2900/07001 , F23D11/107 , F23D11/383 , F23D2900/14021 , F23R3/286 , F23R3/30 , Y02T50/675
Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.
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Patent Agency Ranking
公开(公告)号：US10724741B2
公开(公告)日：2020-07-28
申请号：US15150844
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Shashank Yellapantula , Anthony John Dean , Narendra Digamber Joshi , Mehmet Muhittin Dede , Jin Yan , Owen James Sullivan Rickey
Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.
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公开(公告)号：US20180179961A1
公开(公告)日：2018-06-28
申请号：US15390035
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Thomas Michael Lavertu, Jr. , Kapil Kumar Singh , Venkat Eswarlu Tangirala , Michael John Bowman , Joel Meier Haynes , Anthony John Dean
CPC classification number: F02C9/40 , F02C3/16 , F02C3/165 , F02C3/22 , F02C3/305 , F02C5/00 , F02C5/04 , F02C6/18 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23R3/00 , F23R3/56 , F23R7/00
Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel.
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公开(公告)号：US10352567B2
公开(公告)日：2019-07-16
申请号：US14879793
申请日：2015-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Liangyu Wang , Anthony John Dean , Keith Robert McManus , Kapil Kumar Singh , Suhui Li , Sravan Kumar Dheeraj Kapilavai , Mathew Paul Thariyan , Owen Graham
Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.
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公开(公告)号：US20180340688A1
公开(公告)日：2018-11-29
申请号：US15434830
申请日：2017-02-16
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Jin Yan , Anthony John Dean
IPC: F23R3/28
Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
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公开(公告)号：US20170328569A1
公开(公告)日：2017-11-16
申请号：US15150844
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Shashank Yellapantula , Anthony John Dean , Narendra Digamber Joshi , Mehmet Muhittin Dede , Jin Yan , Owen James Sullivan Rickey
IPC: F23R3/34
Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.
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