公开(公告)号：US20160186998A1

公开(公告)日：2016-06-30

申请号：US14910827

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka, Jr. ,  Randal G. McKinney ,  James B. Hoke ,  Timothy S. Snyder ,  Frank J. Cunha

IPC: F23R3/06 ,  F23R3/00 ,  F02C7/18

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

Abstract: 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 and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

Abstract translation: 用于燃气涡轮发动机的燃烧器的壁组件包括：具有沿着轴线的第一内周边的支撑壳体和具有沿轴线的第二内周边的衬板。 第二内周小于第一内周。 用于燃气涡轮发动机的燃烧器中的另一壁组件包括安装在支撑壳和衬板之间的环形垫圈。 环形垫圈限定了一个轮廓的内壁。

公开(公告)号：US20160178201A1

公开(公告)日：2016-06-23

申请号：US14978044

申请日：2015-12-22

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/26 ,  F23R3/286 ,  F23R2900/03043 ,  F23R2900/03045

Abstract: The present disclosure relates to gas turbine engine components including cooling cavities. One embodiment is directed to a component including a forward surface, an aft surface, at least one inlet on the forward surface and a cavity between the forward surface and the aft surface. The cavity is configured to receive airflow from at least one inlet to provide cooling flow for the component. The cavity includes a plurality of structures within the cavity. The component also includes at least one exit between the forward surface and the aft surface. The plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit. The component having a cavity may be employed by a combustor of a gas turbine engine.

Abstract translation: 本公开涉及包括冷却腔的燃气涡轮发动机部件。 一个实施例涉及包括前表面，后表面，前表面上的至少一个入口和前表面和后表面之间的空腔的部件。 空腔构造成从至少一个入口接收气流以为部件提供冷却流。 空腔包括空腔内的多个结构。 该部件还包括在前表面和后表面之间的至少一个出口。 多个结构被配置为测量空腔内的空气流动并且保持空腔内的空气流从至少一个入口到至少一个出口的冷却效果。 具有空腔的部件可以由燃气涡轮发动机的燃烧器使用。

公开(公告)号：US20160131363A1

公开(公告)日：2016-05-12

申请号：US14935128

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/04 ,  F16C29/02 ,  F23R3/00

CPC classification number: F23R3/04 ,  F16C29/02 ,  F16C2360/23 ,  F23R3/002 ,  F23R3/045 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: An assembly for a turbine engine is provided that includes a combustor wall, which includes an aperture body between a shell and a heat shield. The aperture body at least partially forms a cavity and an aperture that extends through the combustor wall. An inlet passage extends in the combustor wall to the cavity. An outlet passage extends in the combustor wall from the cavity to the aperture.

Abstract translation: 提供了一种用于涡轮发动机的组件，其包括燃烧器壁，燃烧器壁包括壳体和隔热罩之间的孔体。 孔体至少部分地形成延伸穿过燃烧器壁的空腔和孔。 入口通道在燃烧器壁中延伸到空腔。 出口通道在燃烧器壁中从空腔延伸到孔。

公开(公告)号：US20150362192A1

公开(公告)日：2015-12-17

申请号：US14761559

申请日：2013-01-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Nurhak Erbas-Sen

IPC: F23R3/04 ,  F23R3/00

CPC classification number: F23R3/04 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a support shell with a convex profile which faces the heat shield. A further embodiment of the foregoing embodiment of the present disclosure is where the convex profile is defined by a hyperbolic cosine function. A further embodiment of any of the foregoing embodiments of the present disclosure is where the convex profile provides an approximate 4.5 inlet-to-exit area ratio. A further embodiment of any of the foregoing embodiments, of the present disclosure wherein the convex profile provides a flow acceleration toward approximately 0.5 Mach towards an end of a convergent section.

Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的燃烧器的衬套组件包括具有面向隔热罩的凸形轮廓的支撑壳体。 本公开的前述实施例的另一实施例是其中凸形轮廓由双曲余弦函数限定。 本公开的任何前述实施例的另一实施例是凸形轮廓提供大约4.5个入口到出口面积比。 根据本公开的任何前述实施例的另一实施例，其中凸形轮廓提供朝向收敛部分的端部朝向大约0.5马赫的流动加速度。

公开(公告)号：US20150354821A1

公开(公告)日：2015-12-10

申请号：US14647035

申请日：2013-11-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha

IPC: F23R3/04 ,  F23R3/00

CPC classification number: F23R3/04 ,  F02C7/18 ,  F02C7/185 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F23R3/002 ,  F23R3/005 ,  F23R3/02 ,  F23R3/06 ,  F23R3/08 ,  F23R3/42 ,  F23R3/425 ,  F23R3/44 ,  F23R3/46 ,  F23R3/50 ,  F23R3/52 ,  F23R3/54 ,  F23R3/56 ,  F23R3/58 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A combustor having U-shaped cooling channels is disclosed. The combustor may include a shell having an impingement hole, a liner spaced from the shell and having an effusion hole; a first partition spanning between the shell and the liner, a second partition spaced from the first partition and spanning between the shell and the liner; and a U-shaped channel defined between the shell and the liner and defined in part by the wall, the channel having upstream and downstream ends both adjacent the first partition and separated by the wall, wherein the impingement hole communicates with the upstream end and the effusion hole communicates with the downstream end.

Abstract translation: 公开了一种具有U形冷却通道的燃烧器。 燃烧器可以包括具有冲击孔的壳体，与壳体间隔开并具有渗出孔的衬套; 跨越所述壳体和所述衬套之间的第一分隔件，与所述第一分隔件间隔开并跨越所述壳体和所述衬套之间的第二分隔件; 以及U形通道，其限定在所述壳体和所述衬套之间并且部分地由所述壁限定，所述通道具有邻近所述第一隔板的上游和下游端部并被所述壁分隔，其中所述冲击孔与所述上游端和 渗出孔与下游端连通。