利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

722 条记录 (耗时 0.028 秒)

    Electric jet engine
    1.
    发明授权
    Electric jet engine 有权

    公开(公告)号：US12132362B2

    公开(公告)日：2024-10-29

    申请号：US18346765

    申请日：2023-07-03

    申请人： Yuriy Radzikh

    发明人： Yuriy Radzikh

    IPC分类号： F02K5/00 ,  F02C6/00 ,  F23R3/04 ,  H02K16/04

    CPC分类号： H02K16/04 ,  F02K5/00 ,  F02C6/00 ,  F23R3/04

    摘要： Electric engine to provide thrust to fly an aircraft. Engine includes housing, air inlet, shaft, bladed rotor having a plurality of magnets secured on shaft, stator having plurality of coils positioned so as to interact with plurality of magnets and an exhaust nozzle. Powering coils causes interaction with magnets that results in bladed rotor rotating and pressurizing and accelerating air received via air inlet and expelling via exhaust nozzle to provide thrust. Engine may include generator having stator with coils secured to shaft via bearings and plurality of rotors with magnets secured to shaft to rotate with shaft. Magnets rotating past coils results in electric generation. Second hollow shaft may be mounted to shaft with bearings and generator may be located with hollow shaft. Second bladed rotor may be connected to, and rotate, second shaft. Engine may include ducts external to bladed rotor and fan to route air therein.

    COWL ASSEMBLY FOR A GAS TURBINE ENGINE
    2.
    发明公开
    COWL ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230408091A1

    公开(公告)日：2023-12-21

    申请号：US17845472

    申请日：2022-06-21

    申请人： General Electric Company

    发明人： Kishore Ramakrishnan ,  Trevor Howard Wood

    IPC分类号： F23R3/04 ,  F02C7/04 ,  B64D29/06

    CPC分类号： F23R3/04 ,  F02C7/04 ,  B64D29/06 ,  F05D2220/36 ,  B64D33/06

    摘要： An aerodynamic device defining a thickness direction is provided. The aerodynamic device configured to produce lift or thrust or configured to be a part of an aerodynamic system that produces lift or thrust. The aerodynamic device includes a cowl assembly that defines at least in part an airflow stream. The cowl assembly includes a first cowl and a second cowl moveable relative to the first cowl. The first cowl includes a plurality of first cowl indentations at an end of the first cowl. The second cowl defines an outer surface along the thickness direction and an inner surface along the radial direction. The second cowl includes a plurality of second cowl indentations complementary in shape to the plurality of first cowl indentations. The plurality of second cowl indentations are positioned locally on the outer surface of the second cowl or locally on the inner surface of the second cowl.

    Combined cooling heating and power micro gas turbine device
    4.
    发明授权
    Combined cooling heating and power micro gas turbine device 有权

    公开(公告)号：US11815014B2

    公开(公告)日：2023-11-14

    申请号：US17625346

    申请日：2020-12-11

    申请人： TxEGT AUTOMOTIVE POWERTRAIN TECHNOLOGY CO., LTD

    发明人： Pu Jin

    IPC分类号： F02C3/14 ,  F02C6/18 ,  F02C7/06 ,  F02C7/12 ,  F23R3/04

    CPC分类号： F02C3/14 ,  F02C6/18 ,  F02C7/06 ,  F02C7/12 ,  F23R3/04 ,  F05D2220/64 ,  F05D2220/76 ,  F05D2240/52 ,  F05D2240/54

    摘要： A combined cooling heating and power micro gas turbine device includes a micro gas turbine. The micro gas turbine includes a gas compressor, a turbine and a combustion chamber assembly. The combustion chamber assembly includes a combustion chamber, an air inlet cavity, an air inlet channel and an exhaust channel. The air inlet cavity includes an interior air inlet cavity and an exterior air inlet cavity that are integrated, an air outlet end of the exterior air inlet cavity is communicated with an air inlet end of the interior air inlet cavity, an air inlet end of the exterior air inlet cavity is communicated with the air inlet channel, the air inlet channel is communicated with the gas compressor, the combustion chamber is arranged between the interior air inlet cavity and the exterior air inlet cavity, and an air outlet of the combustion chamber is communicated with the exhaust channel.

    Nozzle set
    5.
    发明授权
    Nozzle set 有权

    公开(公告)号：US11795833B1

    公开(公告)日：2023-10-24

    申请号：US18085851

    申请日：2022-12-21

    申请人： PIPL LIMITED

    发明人： Maxym Polyakov

    IPC分类号： F01D9/02 ,  F23R3/04 ,  B33Y80/00

    CPC分类号： F01D9/02 ,  F23R3/04 ,  B33Y80/00 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2240/128

    摘要： An integrated nozzle set for injecting a substance into a turbine is provided. The nozzle set includes an outer nozzle container arranged around a part of a circle and an inner nozzle container having a first part arranged around a remaining part of the circle and a second part concentric with the outer nozzle container. The nozzle set further includes a diaphragm connected to the inner nozzle container and configured to seal a cavity of the turbine, a flange having spokes connected to the inner nozzle container, a set of nozzles, and collectors inserted into the outer nozzle container and configured to collect a substance. The nozzles include a first group of nozzles disposed in the outer nozzle container, a second group of nozzles disposed in the first part of the inner nozzle container, and a third group of nozzles disposed in the second part of the inner nozzle container.

    METHODS OF OPERATING A ROTATING DETONATION COMBUSTOR AT APPROXIMATELY CONSTANT DETONATION CELL SIZE
    6.
    发明申请
    METHODS OF OPERATING A ROTATING DETONATION COMBUSTOR AT APPROXIMATELY CONSTANT DETONATION CELL SIZE 审中-公开

    公开(公告)号：US20180356093A1

    公开(公告)日：2018-12-13

    申请号：US15618380

    申请日：2017-06-09

    申请人： General Electric Company

    发明人： Sibtosh Pal ,  Joseph Zelina ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Steven Clayton Vise

    IPC分类号： F23R3/04 ,  F02C5/12

    CPC分类号： F23R3/04 ,  F02C5/12 ,  F05D2220/32 ,  F05D2240/35

    摘要： 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.

    Damper for combustion oscillation damping in a gas turbine
    9.
    发明授权
    Damper for combustion oscillation damping in a gas turbine 有权

    公开(公告)号：US09970659B2

    公开(公告)日：2018-05-15

    申请号：US14444177

    申请日：2014-07-28

    申请人： ANSALDO ENERGIA IP UK LIMITED

    发明人： Bruno Schuermans ,  Mirko Ruben Bothien

    IPC分类号： F23R3/04 ,  F23R3/00 ,  F02C3/14

    CPC分类号： F23R3/04 ,  F02C3/14 ,  F05D2260/963 ,  F23R3/002 ,  F23R2900/00014

    摘要： The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length Lneck of the neck is equal or greater than a maximum distance lmax that a hot gas ingested from the combustion chamber reaches in the neck. The maximum distance lmax is determined according to the following equation: l max = ∫ t 1 t 2 ⁢ U - p ^ ρ ⁢ ⁢ U ⁢ ⁢ ζ ⁢ sin ⁡ ( ω ⁢ ⁢ t ) ⁢ ⁢ d ⁢ ⁢ t . With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.