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    A gas turbine engine cooling arrangement
    44.
    发明公开
    A gas turbine engine cooling arrangement 有权
    Gasturbinenmotor-Kühlungsanordnung

    公开(公告)号：EP2784267A2

    公开(公告)日：2014-10-01

    申请号：EP14158097.7

    申请日：2014-03-06

    申请人： Rolls-Royce plc

    发明人： Mulcaire, Thomas

    IPC分类号： F01D9/06 ,  F02C7/18

    CPC分类号： F01D25/12 ,  F01D5/082 ,  F01D5/085 ,  F01D9/065 ,  F01D25/246 ,  F02C6/08 ,  F02C7/185 ,  F04D29/321 ,  F04D29/542 ,  F05D2240/90 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    摘要： A gas turbine engine (10) comprises a compressor (14), a combustion chamber (15), an outer casing (20), an inner casing (22) and a cooling arrangement (24). The outer casing (20) surrounds the compressor (14) and the combustion chamber (15) and the combustion chamber (15) has turbine nozzle guide vanes (26). The compressor (14) has load carrying outlet guide vanes (28) connected to the outer casing (20) and the inner casing (22). The turbine nozzle guide vanes (26) connect the outer casing (20) and the inner casing (22). The cooling arrangement (24) comprises a cooling air duct (38) located between the compressor (14) and the combustion chamber (15). The compressor outlet guide vanes (28) carry at least one aerodynamic fairing (40). A support structure (42) supports the cooling air duct (38) from the inner casing (22) at two spaced positions and the support structure (42) forms a chamber (50) with the inner casing (22). The support structure (42) comprises at least one hollow duct (48) and each hollow duct (48) locates behind a respective one of the aerodynamic fairings (40).

    摘要翻译： 燃气涡轮发动机（10）包括压缩机（14），燃烧室（15），外壳（20），内壳（22）和冷却装置（24）。 外壳（20）围绕压缩机（14），燃烧室（15）和燃烧室（15）具有涡轮喷嘴导向叶片（26）。 压缩机（14）具有连接到外壳（20）和内壳（22）的承载出口导叶（28）。 涡轮喷嘴导向叶片（26）连接外壳（20）和内壳（22）。 冷却装置（24）包括位于压缩机（14）和燃烧室（15）之间的冷却空气管道（38）。 压缩机出口导向叶片（28）承载至少一个气动整流罩（40）。 支撑结构（42）在两个间隔位置处从内壳体（22）支撑冷却空气管道（38），并且支撑结构（42）与内壳体（22）形成腔室（50）。 支撑结构（42）包括至少一个中空管道（48），并且每个中空管道（48）位于空气动力学整流罩（40）中的相应一个之后。

    GAS TURBINE
    45.
    发明公开
    GAS TURBINE 审中-公开

    公开(公告)号：EP2309108A4

    公开(公告)日：2014-07-02

    申请号：EP08876707

    申请日：2008-12-24

    申请人： MITSUBISHI HEAVY IND LTD

    发明人： KUBOTA TETSURO ,  TAKAHASHI TATSUJI ,  FUJII KEITA ,  KATSURA HIROTO

    IPC分类号： F02C7/18 ,  F01D25/12 ,  F02C9/18

    CPC分类号： F02C9/18 ,  F01D25/12 ,  F02C7/18 ,  F02C7/185

    摘要： Disclosed is a gas turbine enabling turn down operation, of which the system and the operation can be simplified, and also the production cost and the maintenance cost can be reduced. Specifically disclosed is a gas turbine comprising: a compressor section (2); a combustor section (3); a turbine section (4); a gas turbine casing which houses the compressor section (2), the combustor section (3), and the turbine section (4) therein; a stator cooling air system (5) for leading compressed air extracted from midstream of the compressor section (2) into stator vanes which constitute the turbine section (4); and an air bleeding system (6) for extracting compressed air from the exit of the compressor section (2) to the outside of the gas turbine casing, wherein midstream of the stator cooling air system (5) and midstream of the air bleeding system (6) are connected via a connecting path (12), and at midstream of this connecting path (12), there is a flow rate control part (13) connected.

    Low pressure bleed architecture
    46.
    发明公开
    Low pressure bleed architecture 有权
    Niedrigdruck-Entlüftungsarchitektur

    公开(公告)号：EP2476881A3

    公开(公告)日：2014-04-09

    申请号：EP11195845.0

    申请日：2011-12-28

    申请人： Hamilton Sundstrand Corporation

    发明人： DeFrancesco, Gregory L.

    IPC分类号： F02C6/08

    CPC分类号： F02C9/18 ,  B64D13/06 ,  B64D13/08 ,  B64D2013/0618 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/56

    摘要： A bleed air conditioning system (34;134) within an aircraft including a low-pressure bleed air line (28) and a high-pressure bleed air line (30). The system includes an air-to-air heat exchanger (38) and an un-cooled bleed air line (40) to connect the air-to-air heat exchanger to the low-pressure bleed air line (28) and the high-pressure bleed air line (30). The un-cooled bleed air line (40) carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line (28) and the high-pressure bleed air line (30) to the air-to-air heat exchanger (38). The system also includes a cooled bleed air line (36) connected to the air-to-air heat exchanger (38) for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line (42) connecting the low-pressure bleed air line (28) to the cooled bleed air line (36), bypassing un-cooled bleed air from the low-pressure line (28) around the air-to-air heat exchanger (38) to the cooled bleed air line (36).

    摘要翻译： 一种飞行器内的放气空调系统（34; 134），包括低压排气管线（28）和高压排气管路（30）。 该系统包括空气 - 空气热交换器（38）和未冷却的排放空气管线（40），以将空气 - 空气热交换器连接到低压排气管线（28） 高压排气管路（30）。 未冷却的排气管线（40）将未冷却的排出空气从至少一个低压排气管线（28）和高压排气管线（30）运送至空气 - 至 - 空气热交换器（38）。 该系统还包括连接到空气 - 空气热交换器（38）的冷却的排放空气管线（36），用于承载来自空气 - 空气热交换器的冷却的排放空气和连接 所述低压排放管线（28）连接到所述冷却的排放空气管线（36），绕过所述空气 - 空气热交换器（38）周围的低压管线（28）的未冷却的排出空气绕过所述冷却 排气管（36）。

    Method for operating a combined cycle power plant
    49.
    发明公开
    Method for operating a combined cycle power plant 有权
    Betriebsverfahrenfürein Kombikraftwerk

    公开(公告)号：EP2607634A1

    公开(公告)日：2013-06-26

    申请号：EP12196551.1

    申请日：2012-12-11

    申请人： Alstom Technology Ltd

    发明人： Broesamle, Stefan ,  Ruchti, Christoph

    IPC分类号： F01K23/10 ,  F01D9/06 ,  F02C6/08

    CPC分类号： F01K23/10 ,  F01D19/00 ,  F01K7/16 ,  F01K9/003 ,  F01K23/02 ,  F02C3/04 ,  F02C6/04 ,  F02C6/18 ,  F02C7/14 ,  F02C7/141 ,  F02C7/185 ,  F02C9/18 ,  F05D2220/32 ,  F05D2220/72 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/2322 ,  Y02E20/16

    摘要： In the case of a method for operating a combined cycle power plant (10), which has a gas turbine installation (11) and a water-steam cycle (21) which is connected to the gas turbine installation (11) by means of a waste heat steam generator (24) and has at least one steam turbine (23). The gas turbine installation (11) includes a compressor (13), a combustion chamber (14) and a turbine (16). To cool the turbine (16), air compressed at the compressor (13) is removed, is cooled in at least one cooler (18, 19) flowed through by water thus generating steam and is introduced into the turbine (16). At least with the gas turbine installation (11) running, prior to or during the start-up of the water-steam cycle (21), waste heat which is contained in the steam generated in the at least one cooler (18, 19), is used to good effect for pre-heating the installation inside the combined cycle power plant (10).

    摘要翻译： 在具有燃气轮机装置（11）和通过燃气轮机装置（11）连接到燃气轮机装置（11））的组合循环发电厂（10）的方法的情况下，借助于 废热蒸汽发生器（24）并且具有至少一个汽轮机（23）。 燃气轮机装置（11）包括压缩机（13），燃烧室（14）和涡轮机（16）。 为了冷却涡轮机（16），去除在压缩机（13）处被压缩的空气，在由水流过的至少一个冷却器（18,19）中被冷却，从而产生蒸汽并被引入到涡轮机（16）中。 至少在燃气轮机装置（11）运行时，在水 - 蒸汽循环（21）启动之前或期间，包含在至少一个冷却器（18,19）中产生的蒸汽中的废热， 用于预热联合循环发电厂（10）内部的安装的良好效果。

    Gas turbine engine with controller for cooling and blade tip clearance control of the turbine and coresponding method for operating a gas turbine engine
    50.
    发明公开
    Gas turbine engine with controller for cooling and blade tip clearance control of the turbine and coresponding method for operating a gas turbine engine 审中-公开
    用冷却和控制所述涡轮机的顶端间隙和相关方法燃气涡轮发电设备，

    公开(公告)号：EP2604806A2

    公开(公告)日：2013-06-19

    申请号：EP12193313.9

    申请日：2012-11-20

    申请人： Rolls-Royce plc

    发明人： Bacic, Marko

    IPC分类号： F01D11/24 ,  F01D5/08

    CPC分类号： F01D11/24 ,  F01D5/081 ,  F01D17/02 ,  F01D17/085 ,  F01D25/14 ,  F02C3/13 ,  F02C6/08 ,  F02C7/18 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/205 ,  F05D2270/303 ,  F05D2270/305 ,  F05D2270/44

    摘要： A gas turbine engine (10) with a system (i) for cooling the turbine section and (ii) for providing tip clearance control between turbine blades and the shroud surrounding the turbine blades. The system includes a turbine section cooling sub-system which diverts a first cooling air flow received from the compressor section to a heat exchanger and then to the turbine section to cool components thereof. The first cooling air flow by-passes the combustor (15) and is cooled in the heat exchanger. The turbine section cooling subsystem has a first valve (1) arrangement which regulates the first cooling air flow. The system further includes a tip clearance control sub-system which supplies a second cooling air flow to an engine case to which the segments are mounted. The second cooling air flow regulates thermal expansion of the case and thereby controls the clearance between the shroud and the outer tips. The tip clearance control sub-system has a second valve (2) arrangement which regulates the second cooling air flow. The system further includes a closed-loop controller (K) which issues first and second demand signals to respectively the first and the second valve arrangements (1, 2). Each of the first and second demand signals are determined on the basis of: (i) a value of the first demand signal at a previous time step, and a measurement or estimate of turbine section component temperature, and (ii) a value of the second demand signal at a previous time step, and a measurement or estimate of tip clearance.

    摘要翻译： 一种燃气涡轮发动机（10）与用于冷却涡轮机部分和用于提供涡轮机叶片和包围该涡轮机叶片护罩之间顶隙控制（ⅱ）的系统（i）中。 该系统包括一个涡轮机部分冷却子系统哪个转移从压缩机部分接收到一个热交换器，然后到涡轮部分，以冷却其成分的第一冷却空气流。 第一冷却空气流绕过所述燃烧器（15），并在热交换器中被冷却。 涡轮机部段冷却子系统具有第一阀（1）布置，其调节所述第一冷却空气流。 该系统包括一个另外顶隙控制子系统，其提供第二冷却空气流至在内燃机情况下被安装的段。 第二冷却空气流调控的情况下的热膨胀，从而控制所述护罩和外尖端之间的间隙。 叶尖间隙控制子系统具有第二阀（2）布置，其调节所述第二冷却空气流。 该系统包括一个另外的闭环控制器（K）哪些问题的第一和第二需求信号分别与第一和第二阀装置（1，2）。 每个第一和第二需求信号是确定性的开采的基础上：（i）在先前的时间步长的第一请求信号的值，以及测量或涡轮部分部件温度的估计，和（ii）的一个值 在先前的时间步长的第二请求信号，以及测量或顶端间隙的估计。