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    Bluff body premixing fuel injector and method for premixing fuel and air
    1.
    发明公开
    Bluff body premixing fuel injector and method for premixing fuel and air 有权
    燃料喷射阀与非流线形体和燃料和空气预混合的方法

    公开(公告)号：EP0924463A3

    公开(公告)日：1999-12-08

    申请号：EP98310129.6

    申请日：1998-12-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Morford, Stephen A. ,  van Dyke, Kevin J.

    IPC: F23D17/00 ,  F23C7/00 ,  F23R3/12 ,  F23R3/28

    CPC classification number: F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

    Abstract: A tangential entry premixing fuel injector ( 10 ) for a gas turbine engine combustor includes a pair of offset scrolls ( 18 ) whose ends define a pair of entry slots ( 36 ) for admitting primary combustion air tangentially into a mixing chamber ( 28 ) bounded by the scrolls ( 18 ) and by longitudinally spaced endplates ( 14, 16 ). An array of fuel injection passages ( 42 ) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H . The injector also includes a flame disgorging centerbody ( 48 ) having a bluff tip ( 54 ) longitudinally aligned with the injector's discharge plane ( 22 ) and a secondary fuel conduit ( 80 ) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings ( 84 ) in the tip ( 54 ). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber ( 28 ) and reliably disgorging any flame that is ingested. The controlled fuel penetration depth reinforces the flame disgorging capability of the centerbody by preventing fuel from penetrating into the slowly moving boundary layer attached to the centerbody ( 48 ). The bluff character of the centerbody, in combination with its longitudinal alignment with the fuel injector discharge plane, makes the centerbody capable of anchoring the flame at the discharge plane so that combustion occurs aft of the discharge plane where the combustion flame is unlikely to damage the scrolls or centerbody. Introduction of fuel or fuel and air through the openings in the bluff tip encourage the flame to become anchored to the tip and therefore spatially stabilizes the flame, resulting in additional attenuation of acoustic oscillations and further improved combustor durability. The longitudinally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame stability. The injector and an associated method of premixing fuel and air prior to combustion suppress formation of nitrous oxides, and improve the durability of both the injector and the combustor.

    Noise control cassette for a gas turbine engine
    2.
    发明公开
    Noise control cassette for a gas turbine engine 有权
    Eesatz zur Schallementskontrolle在einer Gurburbine

    公开(公告)号：EP1998003A2

    公开(公告)日：2008-12-03

    申请号：EP08251847.3

    申请日：2008-05-28

    Applicant: United Technologies Corporation

    Inventor： Reba, Ramons A. ,  Morford, Stephen A. ,  Morin, Bruce L. ,  Lord, Wesley K.

    IPC: F01D5/16

    CPC classification number: F01D9/02 ,  F02C7/24 ,  F02K1/827 ,  F04D29/324 ,  F04D29/665 ,  F04D29/681 ,  F05B2220/709 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2260/96 ,  F05D2260/963

    Abstract: A noise control cassette (40) for a gas turbine engine (20) includes a perforated face sheet (50) configured for exposure to an airflow, a non-perforated backing sheet (52), a core (54A) arranged between the face sheet (50) and the backing sheet (52) and defining a cavity (62) between the face sheet (50) and the backing sheet (52) having an effective length (L) tuned so as to provide acoustic reactance control, and an attachment face (56) for attaching the cassette to an airfoil-shaped structure (44).

    Abstract translation: 用于燃气涡轮发动机（20）的噪声控制盒（40）包括被配置为暴露于气流的穿孔面片（50），非穿孔背衬片（52），布置在面板 （50）和所述背衬片（52），并且在所述面片（50）和所述背衬片（52）之间限定具有调谐以提供声电抗控制的有效长度（L）的空腔（62），以及附件 面板（56），用于将盒子附接到翼型结构（44）。

    Bluff body premixing fuel injector and method for premixing fuel and air
    3.
    发明公开
    Bluff body premixing fuel injector and method for premixing fuel and air 有权
    一种燃料喷射器与非流线形体和燃料和空气预混合的方法

    公开(公告)号：EP1340942A2

    公开(公告)日：2003-09-03

    申请号：EP03008697.9

    申请日：1998-12-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Synder, Timothy S. ,  Morford, Stephen A. ,  Sowa, William A. ,  Van Dyke, Kevin J.

    IPC: F23R3/28 ,  F23R3/12 ,  F23C7/00 ,  F23D17/00

    CPC classification number: F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

    Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14,16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested.

    Abstract translation: 切向入口预混合燃料喷射器（10），用于燃气涡轮发动机燃烧器包括用于沿切向接纳主燃烧空气进入由界定的混合室（28），其端部限定的一对进入槽（36）的一对偏置卷轴（18） 涡旋盘（18），并通过纵向隔开的端板（14,16）。 燃料喷射通路阵列（42），沿着所述槽的长度上延伸。 通道阵列被配置为沿所述空气进入槽的长度不均匀地喷射一次燃料，并且控制燃料贯穿深度d成正比槽高度H.因此，该喷射器包括火焰除渣中心体（48）具有钝尖（ 54）与喷射器的排放平面（22）和二次燃料导管（80）穿过所述中心体延伸，用于放电的二次可燃流体，优选气体燃料，通过一系列在尖端燃料排放口（84）的（54纵向对齐 ）。 火焰除渣中心体通过抵抗燃烧火焰吸入到混合腔（28）和可靠除渣任何火焰都被摄入提高燃料喷射器的耐久性。

    Method of combustion with a two stream tangential entry nozzle
    5.
    发明公开
    Method of combustion with a two stream tangential entry nozzle 失效
    与切向Zweistromdüse燃烧过程

    公开(公告)号：EP0849527A3

    公开(公告)日：1999-06-09

    申请号：EP97310459.9

    申请日：1997-12-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kramer, Stephen K. ,  Morford, Stephen A. ,  Graves, Charles B.

    IPC: F23C7/00 ,  F23D17/00

    CPC classification number: F23C7/002 ,  F05B2250/322 ,  F23C2900/07002 ,  F23D17/002 ,  F23D2206/10

    Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler (14) having first and second endplates (16,18), the first endplate is spaced relation to the second endplate defining a substantially cylindrical mixing zone (28) therebetween, the second endplate having a combustor inlet port (20) extending therethrough, providing a centerbody (12) located within the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously along the length thereof, introducing a first portion of fuel into the combustion air as the combustion air is introduced into the mixing zone, mixing the combustion air and fuel by swirling the combustion air and fuel about the centerbody while flowing the combustion air and fuel towards the combustor inlet, flowing the first portion of combustion air into the combustor inlet, introducing a second portion of combustion air into the first portion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.

    Bluff body premixing fuel injector and method for premixing fuel and air
    7.
    发明公开
    Bluff body premixing fuel injector and method for premixing fuel and air 有权
    Brennstoffeinspritzventil und Verfahren zur Vormischung von Brennstoff und Luft

    公开(公告)号：EP0924463A2

    公开(公告)日：1999-06-23

    申请号：EP98310129.6

    申请日：1998-12-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Morford, Stephen A. ,  van Dyke, Kevin J.

    IPC: F23D17/00 ,  F23C7/00 ,  F23R3/12 ,  F23R3/28

    CPC classification number: F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

    Abstract: A tangential entry premixing fuel injector ( 10 ) for a gas turbine engine combustor includes a pair of offset scrolls ( 18 ) whose ends define a pair of entry slots ( 36 ) for admitting primary combustion air tangentially into a mixing chamber ( 28 ) bounded by the scrolls ( 18 ) and by longitudinally spaced endplates ( 14, 16 ). An array of fuel injection passages ( 42 ) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H . The injector also includes a flame disgorging centerbody ( 48 ) having a bluff tip ( 54 ) longitudinally aligned with the injector's discharge plane ( 22 ) and a secondary fuel conduit ( 80 ) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings ( 84 ) in the tip ( 54 ). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber ( 28 ) and reliably disgorging any flame that is ingested. The controlled fuel penetration depth reinforces the flame disgorging capability of the centerbody by preventing fuel from penetrating into the slowly moving boundary layer attached to the centerbody ( 48 ). The bluff character of the centerbody, in combination with its longitudinal alignment with the fuel injector discharge plane, makes the centerbody capable of anchoring the flame at the discharge plane so that combustion occurs aft of the discharge plane where the combustion flame is unlikely to damage the scrolls or centerbody. Introduction of fuel or fuel and air through the openings in the bluff tip encourage the flame to become anchored to the tip and therefore spatially stabilizes the flame, resulting in additional attenuation of acoustic oscillations and further improved combustor durability. The longitudinally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame stability. The injector and an associated method of premixing fuel and air prior to combustion suppress formation of nitrous oxides, and improve the durability of both the injector and the combustor.

    Abstract translation: 用于燃气涡轮发动机燃烧器的切向入口预混合燃料喷射器（10）包括一对偏置涡卷（18），其一端限定一对入口槽（36），用于将初级燃烧空气切向地进入混合室（28） 涡卷（18）和纵向隔开的端板（14,16）。 燃料喷射通道（42）的阵列沿槽的长度延伸。 通道阵列被构造成沿着空气入口狭槽的长度不均匀地喷射一次燃料，并且与槽高度H成比例地控制燃料穿透深度D.喷射器还包括具有虚张出风口尖端的火焰释放中心体（48） 54），其与喷射器的排出平面（22）纵向对齐，以及延伸穿过中心体的次级燃料导管（80），用于通过尖端（54）中的一系列燃料排放开口（84）排出次级可燃液体，优选气体燃料 ）。 火焰喷射中心体通过阻止燃烧火焰进入混合室（28）并可靠地排除任何被摄入的火焰来提高燃料喷射器的耐久性。 受控的燃料穿透深度通过防止燃料渗透到附接到中心体（48）的缓慢移动的边界层中，加强了中心体的火焰排出能力。 中心体的虚张声势特征与其与燃料喷射器排放平面的纵向对准结合使得中心体能够将火焰锚定在排放平面处，使得燃烧发生在排放平面的后方，其中燃烧火焰不太可能损坏 卷轴或中心体。 燃料或燃料和空气通过虚张声光尖端的开口引入，促使火焰锚定到尖端，从而在空间上稳定火焰，从而进一步衰减声振荡并进一步提高燃烧器的耐久性。 主要燃料的纵向不均匀喷射补偿了归因于火焰排出中心体的任何混合不均匀性，因此增加了火焰稳定性。 喷射器和在燃烧之前预混合燃料和空气的相关方法抑制了一氧化二氮的形成，并提高了喷射器和燃烧器的耐久性。

    Method of combustion with a two stream tangential entry nozzle
    8.
    发明公开
    Method of combustion with a two stream tangential entry nozzle 失效
    Verbrennungsverfahren mit einer tangentialenZweistromdüse

    公开(公告)号：EP0849527A2

    公开(公告)日：1998-06-24

    申请号：EP97310459.9

    申请日：1997-12-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kramer, Stephen K. ,  Morford, Stephen A. ,  Graves, Charles B.

    IPC: F23C7/00 ,  F23D17/00

    CPC classification number: F23C7/002 ,  F05B2250/322 ,  F23C2900/07002 ,  F23D17/002 ,  F23D2206/10

    Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler (14) having first and second endplates (16,18), the first endplate is spaced relation to the second endplate defining a substantially cylindrical mixing zone (28) therebetween, the second endplate having a combustor inlet port (20) extending therethrough, providing a centerbody (12) located within the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously along the length thereof, introducing a first portion of fuel into the combustion air as the combustion air is introduced into the mixing zone, mixing the combustion air and fuel by swirling the combustion air and fuel about the centerbody while flowing the combustion air and fuel towards the combustor inlet, flowing the first portion of combustion air into the combustor inlet, introducing a second portion of combustion air into the first portion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.

    Abstract translation: 一种用燃烧涡轮发动机的燃烧器中的燃料燃烧的方法，该燃料涡轮发动机具有预混燃烧类型，其包括提供具有第一和第二端板（16,18）的涡旋旋流器（14），所述第一端板与所述第二端板间隔开，所述第二端板限定 其间的基本上圆柱形的混合区（28），所述第二端板具有延伸穿过其中的燃烧器入口（20），提供位于所述混合区内的中心体（12），并具有朝向所述燃烧器入口变细的径向外表面， 混合区的整个长度，沿着其长度基本连续地将燃烧空气的第一部分切向地引入混合区，当燃烧空气被引入混合区时，将第一部分燃料引入燃烧空气中， 燃烧空气和燃料通过在燃烧空气和燃料流向燃烧空气和燃料的同时将燃烧空气和燃料围绕中心体旋转 燃烧器入口将燃烧空气的第一部分流入燃烧器入口，将燃烧空气的第二部分在燃烧器入口处径向向内的第一部分引入，燃烧空气的第一和第二部分之和限定总气流，以及 燃烧空气的第二部分等于总气流的85-89％，并燃烧混合区域外部的燃料。

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