公开(公告)号：US20160003478A1

公开(公告)日：2016-01-07

申请号：US14789557

申请日：2015-07-01

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Stanislav Kostka, JR.

IPC: F23R3/14 ,  F23R3/00

CPC classification number: F23R3/14 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A dilution hole assembly that may be of a combustor has a first wall that defines a hole that may communicate through a liner and outer shell of the combustor for flowing dilution air from an air plenum located outward of the shell and into a combustion chamber defined by and located inward of the liner. The assembly has an outer wall that may be engaged to the shell and liner, and which defines the hole. An inner wall of the assembly may be in the hole such that an annular portion of the hole is defined between the inner and outer walls. A plurality of vanes may be in the annular portion and spaced from one-another for swirling air that flows through the annular portion. The walls may be generally conical in shape and/or radially sloped such that air flowing through the annular portion and air flowing at least through the inner portion impinge upon one-another adding to the air turbulence created by the swirling action of the vanes and thus enhancing efficient combustion and temperature profiling within the combustion chamber.

Abstract translation: 可以是燃烧器的稀释孔组件具有第一壁，其限定可以通过燃烧器的衬套和外壳连通的孔，用于将稀释空气从位于壳体外部的空气室排出并进入由壳体外部限定的燃烧室 并位于内衬的内侧。 组件具有外壁，其可以接合到壳体和衬套，并且限定孔。 组件的内壁可以在孔中，使得孔的环形部分限定在内壁和外壁之间。 多个叶片可以在环形部分中并且彼此间隔开以流过环形部分的旋转空气。 壁可以是大致圆锥形的和/或径向倾斜的，使得流过环形部分的空气和至少通过内部部分流动的空气彼此撞击，从而增加由叶片的旋动作用产生的空气湍流，因此 提高燃烧室内的有效燃烧和温度分布。

公开(公告)号：US20160273771A1

公开(公告)日：2016-09-22

申请号：US15034689

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F01D5/188 ,  F01D9/023 ,  F01D25/12 ,  F02C7/18 ,  F02C7/24 ,  F05D2250/21 ,  F05D2250/23 ,  F05D2250/232 ,  F05D2250/24 ,  F05D2250/241 ,  F05D2250/324 ,  F05D2250/712 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214 ,  F23R3/005 ,  F23R2900/03042

Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括外壳和在外壳和隔热罩之间具有冷却腔的隔热罩。 隔热罩限定了多个冷却孔和位于热屏蔽的与冷却腔相对的一侧的凹陷。 冷却孔与冷却腔流体耦合。 压痕被配置成使得从第一冷却孔引导的冷却空气至少部分地与隔热板的侧面循环。

公开(公告)号：US20160238249A1

公开(公告)日：2016-08-18

申请号：US15025455

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06

CPC classification number: F23R3/002 ,  F02C7/18 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.

Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧器壁包括外壳，隔热罩和冷却元件。 外壳限定了第一组孔。 隔热罩限定第二组孔。 冷却元件在外壳和隔热罩之间延伸在限定在外壳和隔热罩之间的锥形冷却腔内。 锥形空腔与第一组和第二组孔流体连接。 冷却元件热耦合到外壳和隔热罩中的一个。

公开(公告)号：US20160201908A1

公开(公告)日：2016-07-14

申请号：US14910856

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher Drake ,  Frank J. Cunha ,  Stanislav Kostka, JR. ,  Jonathan M. Jause ,  Russell B. Hanson

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/26 ,  F02C7/18

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，其包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

公开(公告)号：US20160102861A1

公开(公告)日：2016-04-14

申请号：US14893378

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

IPC: F23R3/00 ,  F23R3/06

Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmentation feature with a second heat transfer augmentation feature stacked thereon.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括多个从其冷侧延伸的传热增强器。 多个传热增强器中的至少一个包括具有堆叠在其上的第二传热增强特征的第一传热增强特征。

公开(公告)号：US20150285498A1

公开(公告)日：2015-10-08

申请号：US14677520

申请日：2015-04-02

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka, JR. ,  Andreas Sadil

IPC: F23R3/06 ,  F02C7/18

Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.

Abstract translation: 一种用于提高其流动系数的护环组件和设计方法包括具有第一侧和相对的第二侧的壳体，以及沿着中心线突出穿过壳体的倒角索环，并且包括从第二侧向外间隔开的环形第一端表面 第一侧和圆锥形表面从环形第一端表面轴向和径向向内跨过并且轴向地超过第二侧。 组件还可以包括与壳体间隔开并且在其间限定冷却腔的面板，锥形表面至少部分地限定通过壳体和面板流体连通并与冷却腔隔离的孔。 索环中的多个冷却通道与冷却腔流体连通并通过面板连通。 锥形面和冷却通道的组合提高了垫圈的排气系数，同时增强了索环冷却。