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123 条记录 (耗时 0.019 秒)

    Fuel control system
    1.
    发明授权
    Fuel control system 有权

    公开(公告)号：US11891959B2

    公开(公告)日：2024-02-06

    申请号：US17983874

    申请日：2022-11-09

    申请人： ROLLS-ROYCE plc

    发明人： Daniel J Bickley

    IPC分类号： F02C9/00 ,  F02C9/26 ,  F02C9/46 ,  F02C7/232

    CPC分类号： F02C9/263 ,  F02C7/232 ,  F02C9/46 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/05 ,  F05D2270/07

    摘要： A fuel control system for a gas turbine engine includes a fuel metering valve, a pressure raising and shut-off valve (PRSOV), and a shutoff effector including a first stage unit that is electrically powered and a second stage unit that is controlled by the first stage unit. The second stage unit actuates a valve member of the PRSOV between an open position that allows supply of a fuel to burners of the gas turbine engine and a closed position that prevents supply of the fuel to the burners. Upon loss of electrical power to the first stage unit during operation of the gas turbine engine, the first stage unit is configured to: control the second stage unit to actuate the valve member of the PRSOV to the closed position after a predetermined time duration; or retain the valve member of the PRSOV in the open position.

    TIP CLEARANCE CONTROL FOR TURBINE BLADES
    6.
    发明申请
    TIP CLEARANCE CONTROL FOR TURBINE BLADES 审中-公开
    涡轮叶片尖端间隙控制

    公开(公告)号：US20160169026A1

    公开(公告)日：2016-06-16

    申请号：US14967875

    申请日：2015-12-14

    申请人： ROLLS-ROYCE plc

    发明人： Simon Lloyd JONES

    IPC分类号： F01D11/24 ,  F01D25/28 ,  F01D25/24 ,  F01D5/12 ,  F01D25/14

    CPC分类号： F01D11/24 ,  F01D5/12 ,  F01D25/14 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2240/24 ,  F05D2260/201 ,  F05D2260/30 ,  F05D2270/07 ,  F05D2270/20

    摘要： An engine includes circumferentially spaced turbine blades radially inward a casing and circumscribed by a carrier section having segments, each having a carrier wall radially inward the casing and radially outward the turbine blades. The wall has one or more portions facing the casing. At least one of the portions has one or more impingement apertures for air passage of a predetermined temperature from a feed source into impingement onto the casing. The segments are radially inward the casing and radially outward the turbine blades, with the portions of their respective walls facing the casing. A method of controlling the gas turbine engine turbine casing temperature includes: passing air of a predetermined temperature from a feed source through the apertures in the one or more portions and into impingement on the casing; and optionally exhausting the air impinged onto the casing from a space between the segment and the casing.

    摘要翻译： 发动机包括周向间隔开的涡轮机叶片，其径向向内设置有壳体并由具有段的承载部分限定，每个承载部分具有径向向内的壳体和径向向外的涡轮叶片。 壁具有面向壳体的一个或多个部分。 这些部分中的至少一个具有一个或多个冲击孔，用于将来自进料源的预定温度的空气通过到冲击到壳体上。 这些段沿壳体径向向内并且涡轮叶片径向向外，其各自壁的部分面向壳体。 控制燃气涡轮发动机涡轮机壳体温度的方法包括：使来自进料源的预定温度的空气通过所述一个或多个部分中的孔并且进入到壳体上的冲击; 并且可选地从所述段和所述壳体之间的空间排出撞击到所述壳体上的空气。

    ENGINE FUEL CONTROL SYSTEM
    7.
    发明申请
    ENGINE FUEL CONTROL SYSTEM 有权
    发动机燃油控制系统

    公开(公告)号：US20150192075A1

    公开(公告)日：2015-07-09

    申请号：US14528562

    申请日：2014-10-30

    申请人： ROLLS-ROYCE CONTROLS AND DATA SERVICES LIMITED

    发明人： Michael GRIFFITHS

    IPC分类号： F02C9/30 ,  F02C9/28

    CPC分类号： F02C9/30 ,  F01D19/00 ,  F02C7/236 ,  F02C7/26 ,  F02C9/28 ,  F02C9/32 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/03 ,  F05D2270/07 ,  F05D2270/304 ,  F05D2270/56 ,  F05D2270/64 ,  F05D2270/66 ,  Y02T50/671

    摘要： An engine fuel control system includes a fuel metering valve that controls the flow of fuel between supply and delivery lines which delivers fuel to engine burners. The fuel control system includes a fixed displacement main pump which receives fuel from a low pressure source and delivers the fuel at a first high pressure to the supply line, an augmenter pump which receives fuel from the low pressure source and delivers the fuel at a second high pressure to one or more fuel-pressure operated auxiliary engine devices, and a start valve which is actuated at low engine speeds to open a flow path which diverts fuel delivered by the augmenter pump away from the auxiliary engine devices to the supply line to augment the fuel delivered thereto by the main pump, the start valve being actuated at higher engine speeds to shut the flow path.

    摘要翻译： 发动机燃料控制系统包括燃料计量阀，其控制在将燃料输送到发动机燃烧器的供应和输送管线之间的燃料流动。 燃料控制系统包括固定排量主泵，其从低压源接收燃料并将燃料以第一高压输送到供应管线;增压泵，其从低压源接收燃料并在第二高压源处输送燃料 一个或多个燃料压力操作的辅助发动机装置的高压，以及以低发动机转速致动的起动阀，以打开将由增压泵输送的燃料从辅助发动机装置转移到供应管线以增加的流动路径 由主泵输送的燃料，起动阀以更高的发动机转速被致动以关闭流路。

    Critical flow nozzle for controlling fuel distribution and burner stability
    8.
    发明授权
    Critical flow nozzle for controlling fuel distribution and burner stability 有权
    用于控制燃料分配和燃烧器稳定性的临界流量喷嘴

    公开(公告)号：US08776529B2

    公开(公告)日：2014-07-15

    申请号：US12891358

    申请日：2010-09-27

    申请人： Bruce Paradise

    发明人： Bruce Paradise

    IPC分类号： F02C1/00

    CPC分类号： F02C9/32 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2240/128 ,  F05D2240/40 ,  F05D2260/96 ,  F05D2270/07

    摘要： A fuel delivery system for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle, a first fuel nozzle and a second fuel nozzle. The fixed critical flow nozzle and the variable critical flow nozzle are connected to a fuel source in parallel. The fixed critical flow nozzle has an orifice throat with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat with a variable effective cross-sectional area. The first fuel nozzle is connected to the fixed critical flow nozzle for delivering fuel to the gas turbine engine, and the second fuel nozzle is connected to the variable critical flow nozzle for delivering fuel to the gas turbine engine.

    摘要翻译： 用于将燃料输送到燃气涡轮发动机的燃料输送系统包括固定临界流喷嘴，第一燃料喷嘴和第二燃料喷嘴。 固定临界流喷嘴和可变临界流喷嘴并联连接到燃料源。 固定临界流喷嘴具有具有固定的有效横截面面积的孔喉。 可变临界流喷嘴具有具有可变有效横截面积的孔喉。 第一燃料喷嘴连接到用于将燃料输送到燃气涡轮发动机的固定临界流动喷嘴，并且第二燃料喷嘴连接到用于将燃料输送到燃气涡轮发动机的可变临界流喷嘴。

    AEROSPACE ENGINE WITH AUGMENTING TURBOJET
    9.
    发明申请
    AEROSPACE ENGINE WITH AUGMENTING TURBOJET 有权
    航空发动机带有增压涡轮

    公开(公告)号：US20130239576A1

    公开(公告)日：2013-09-19

    申请号：US13421241

    申请日：2012-03-15

    申请人： Daniel Bernard Kupratis ,  Joseph B. Staubach

    发明人： Daniel Bernard Kupratis ,  Joseph B. Staubach

    IPC分类号： F02C3/04 ,  F02C9/16

    CPC分类号： F02C3/04 ,  F02C3/13 ,  F02C6/00 ,  F02C6/02 ,  F02C9/18 ,  F02K3/12 ,  F05D2250/30 ,  F05D2250/311 ,  F05D2270/07

    摘要： A gas turbine engine system includes a fan section, a low pressure compressor section downstream of the fan section, a first engine core downstream from the low pressure compressor section, a second engine core downstream from the low pressure compressor section, and a flowpath control mechanism configured to selectively restrict fluid flow through the second engine core. The first engine core includes a first engine core compressor section, a first engine core combustor downstream of the first engine core compressor section, and a first engine core turbine section downstream of the first engine core combustor. The second engine core includes a second engine core compressor section, a second engine core combustor downstream of the second engine core compressor section, and a second engine core turbine section downstream of the second engine core combustor.

    摘要翻译： 燃气涡轮发动机系统包括风扇部分，风扇部分下游的低压压缩机部分，低压压缩机部分下游的第一发动机芯，低压压缩机部分下游的第二发动机芯，以及流路控制机构 被配置为选择性地限制流过第二发动机芯的流体。 第一发动机机芯包括第一发动机核心压缩机部分，第一发动机核心压缩机部分下游的第一发动机核心燃烧器和第一发动机核心燃烧器下游的第一发动机芯涡轮机部分。 第二发动机机芯包括第二发动机芯压缩机部分，第二发动机芯压缩机部分下游的第二发动机核心燃烧器和第二发动机芯燃烧器下游的第二发动机芯涡轮机部分。