公开(公告)号：US20160123594A1

公开(公告)日：2016-05-05

申请号：US14932556

申请日：2015-11-04

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/06 ,  F02C7/18 ,  F23R3/00

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a first layer vertically connected with a second layer. A first portion of the first layer overlaps and is vertically spaced from the second layer by a cavity. A second portion of the first layer is substantially vertically inline with an adjacent portion of the second layer. The second portion of the first layer at least partially forms a quench aperture vertically through the combustor wall.

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燃烧器壁，该燃烧器壁包括与第二层垂直连接的第一层。 第一层的第一部分与空腔重叠并与第二层垂直间隔开。 第一层的第二部分基本上与第二层的相邻部分垂直一致。 第一层的第二部分至少部分地通过燃烧器壁垂直地形成骤冷孔。

公开(公告)号：US20160123592A1

公开(公告)日：2016-05-05

申请号：US14897725

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher Drake ,  Frank J Cunha ,  Stanislav Kostka

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.

Abstract translation: 为燃气涡轮发动机的燃烧器提供衬套面板。 衬板包括多个传热增强器。 多个传热增强器中的至少一个包括凹陷，其中凹陷包括穿过衬垫板的至少一个通道的入口。

公开(公告)号：US20160003477A1

公开(公告)日：2016-01-07

申请号：US14790970

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷却孔结构，并且还可以是稀释孔结构，包括热侧板，与热侧板间隔开的冷侧板，以及连续的内壁，其延伸 在热和冷侧板之间并且限定具有中心线并且轴向地通过热和冷侧板的孔口。 该结构的多个端壁位于由冷热侧板和内壁部分限定的冷却腔中。 每个端壁在热侧面板和冷侧面板之间延伸并与之接合，并与下一个相邻的端壁沿圆周间隔开。 多个入口孔延伸穿过冷侧面板并且与空腔流体连通，并且多个入口孔中的每一个靠近多个端壁中的相应一个的第一侧。 多个出口孔延伸穿过热侧面板并且与空腔流体连通，并且多个出口孔中的每一个与多个端壁中的相应一个端壁的相对的第二侧相关联。