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Patent Agency Ranking
公开(公告)号：US20180356094A1
公开(公告)日：2018-12-13
申请号：US15618431
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Joseph Zelina , Sibtosh Pal , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a method of operating a propulsion system at an approximately constant detonation cell quantity in the combustion chamber of a detonation combustion system. The propulsion system defines an inlet section upstream of the rotating detonation combustion system and an exhaust section downstream of the rotating detonation combustion system. The method includes providing an outer wall and an inner wall together defining an annular gap and a combustion chamber length extended from a combustion chamber inlet proximate to the fuel-oxidizer mixing nozzle to a combustion chamber exit proximate to the exhaust section of the propulsion system, the annular gap and the combustion chamber length together defining a first volume at a first operating condition defining a lowest steady state pressure and temperature at the rotating detonation combustion system; providing a mixture of a fuel and an oxidizer to the combustion chamber via the fuel-oxidizer mixing nozzle; detonating the fuel and oxidizer mixture in the combustion chamber, wherein the detonation produces a detonation cell size; and adjusting the volume of the combustion chamber via articulating one or more of the outer wall, the inner wall, and the fuel-oxidizer mixing nozzle such that one or more of the annular gap and the combustion chamber length is changed based on one or more operating conditions.
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62.发明申请公开(公告)号：US20180356093A1
公开(公告)日：2018-12-13
申请号：US15618380
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
CPC classification number: F23R3/04 , F02C5/12 , F05D2220/32 , F05D2240/35
Abstract: The present disclosure is directed to a method of operating a propulsion system including a rotating detonation combustion (RDC) system. The RDC system defines a combustion inlet at an upstream end, a combustion outlet at a downstream end, a combustion chamber therebetween, and a nozzle defined at the combustion inlet upstream of the combustion chamber, and a secondary flowpath extended from upstream of the nozzle to downstream of the nozzle. The method includes providing the combustion chamber of the rotating detonation combustion system to produce a detonation cell size configured for a first operating condition defining a lowest steady state operating condition of the propulsion system; generating a flow of oxidizer to the combustion inlet of the combustion section; providing a first portion of the flow of oxidizer to the combustion chamber and mixing the first portion of the flow of oxidizer with a fuel; providing a second portion of the flow of oxidizer to the secondary flowpath, wherein the secondary flowpath bypasses the combustion chamber; and adjusting a ratio of the first portion of the flow of oxidizer through the combustion chamber versus the second portion of the flow of oxidizer through the secondary flowpath based at least on a commanded power output of the propulsion system.
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公开(公告)号：US20180355792A1
公开(公告)日：2018-12-13
申请号：US15618495
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The rotating detonation combustion system includes an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining at least in part a combustion chamber and a combustion chamber inlet. The outer wall and the inner wall together define an annular nozzle concentric to the longitudinal centerline at the combustion chamber inlet. The nozzle defines a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and nozzle outlet. The rotating detonation combustion system further includes a fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to the flow of oxidizer received through the nozzle inlet.
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公开(公告)号：US20180231256A1
公开(公告)日：2018-08-16
申请号：US15429655
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Johnson , Clayton S. Cooper , Steven Vise
CPC classification number: F23R7/00 , F02C5/02 , F02C7/264 , F02K3/06 , F05D2220/32 , F05D2240/35
Abstract: A rotating detonation combustion system includes an outer wall and an inner wall together defining at least in part a combustion chamber and a combustion chamber inlet. A nozzle of the rotating detonation combustion system is located at the combustion chamber inlet, the nozzle defining a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction. The nozzle further defines a throat between the nozzle inlet and nozzle outlet. A fuel injection port is also provided, the fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to a flow of oxidizer received through the nozzle inlet.
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公开(公告)号：US20170350598A1
公开(公告)日：2017-12-07
申请号：US15172590
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina
CPC classification number: F23R3/286 , F02C7/222 , F23R3/14 , F23R3/16 , Y02T50/675
Abstract: The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the outer sleeve, and at least one axially oriented vane defined between the centerbody and a section of the inner sleeve. A section of the outer sleeve includes at least one radially oriented vane. A portion of the inner sleeve includes a contoured shroud and defines at least one fuel injection port disposed upstream of the contoured shroud. The axially oriented vane is disposed upstream of the fuel injection port.
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