公开(公告)号：US20170184306A1

公开(公告)日：2017-06-29

申请号：US14982642

申请日：2015-12-29

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Jonathan Jeffery Eastwood ,  Kevin Joseph Low ,  Sean D. Bradshaw

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/005 ,  F23R3/002 ,  F23R3/06 ,  F23R3/26 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03043

Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.

公开(公告)号：US20160222794A1

公开(公告)日：2016-08-04

申请号：US14917879

申请日：2014-09-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mark F. Zelesky ,  Atul Kohli ,  Sean D. Bradshaw ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/08 ,  F04D29/32 ,  F04D29/58 ,  F04D29/54 ,  F01D5/14 ,  F01D11/08

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F04D29/083 ,  F04D29/324 ,  F04D29/325 ,  F04D29/542 ,  F04D29/5846 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/204

Abstract: This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side. The component further includes a first core passageway and a second core passageway separate from the first core passageway. The first core passageway and the second core passageway are in communication with a respective one of the first group of showerhead holes and the second group of showerhead holes.

Abstract translation: 本公开涉及一种燃气涡轮发动机，其包括具有前缘，压力侧和与压力侧相对的吸力侧的部件。 该部件包括在前缘中的第一组喷头孔和在压力侧和吸力侧之一中的第二组喷头孔。 该部件还包括与第一芯通道分开的第一芯通道和第二芯通道。 第一芯通道和第二芯通道与第一组喷头孔和第二组喷头孔中的相应一个连通。

公开(公告)号：US20160177735A1

公开(公告)日：2016-06-23

申请号：US14965329

申请日：2015-12-10

Applicant: United Technologies Corporation

Inventor： Sean D. Bradshaw

IPC: F01D5/18 ,  F02C3/04 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/20 ,  F05D2240/303 ,  F05D2240/307 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1. The Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).

Abstract translation: 涡轮叶片包括具有由两个平台周向侧连接的平台前缘和后缘的平台。 机翼从平台径向向外延伸到自由尖端。 翼型件包括通过相对的压力和吸力侧连接的翼型件前缘和后缘。 根从平台向内径向延伸。 平台和翼型件包括具有大体上符合表1所示的笛卡尔坐标的外部突出点的膜冷却孔。由轴向坐标，圆周坐标和径向坐标提供的笛卡尔坐标相对于 零坐标，并且冷却孔相对于0.200英寸（5.0mm）的指定坐标具有径向表面公差。