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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：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：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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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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