公开(公告)号：US09239166B2

公开(公告)日：2016-01-19

申请号：US13663133

申请日：2012-10-29

Applicant: Solar Turbines Incorporated

Inventor： Timothy James Caron ,  Peter J. Skyes ,  Christopher J. Meyer ,  Federico Liberatore

IPC: F23R3/26 ,  F23R3/04

CPC classification number: F23R3/26 ,  F23R3/04 ,  F23R2900/00016 ,  Y10T29/49323

Abstract: A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity.

Abstract translation: 一种用于燃气涡轮发动机的扩散器，扩散器具有第一壁，第二壁和流动分离器。 第一和第二壁限定环形空腔，环形空腔具有入口。 第一和第二壁还形成靠近入口的预扩散器，以及远离入口的倾倒区域。 流动分离器从第一壁延伸到环形空腔中。

公开(公告)号：US20140116056A1

公开(公告)日：2014-05-01

申请号：US13663133

申请日：2012-10-29

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Timothy James Caron ,  Peter J. Skyes ,  Christopher J. Meyer ,  Federico Liberatore

IPC: F23R3/26 ,  B21D53/00

CPC classification number: F23R3/26 ,  F23R3/04 ,  F23R2900/00016 ,  Y10T29/49323

Abstract: A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity.

Abstract translation: 一种用于燃气涡轮发动机的扩散器，扩散器具有第一壁，第二壁和流动分离器。 第一和第二壁限定环形空腔，环形空腔具有入口。 第一和第二壁还形成靠近入口的预扩散器，以及远离入口的倾倒区域。 流动分离器从第一壁延伸到环形空腔中。

公开(公告)号：US20140099190A1

公开(公告)日：2014-04-10

申请号：US13646526

申请日：2012-10-05

Applicant: SOLAR TURBINES INCORPORATED

Inventor： Christopher J. Meyer ,  Tsuhon Lin ,  Edward T. Ramirez

IPC: F01D25/14 ,  B23P6/00

CPC classification number: F01D25/14 ,  Y10T29/49726 ,  Y10T29/49732

Abstract: A turbine housing (430) includes a support housing (440) with an annular shape. The support housing (432) includes an outer surface (433) and an inner surface (434). The inner surface (434) is located radially inward from the outer surface (433). A plurality of cooling holes (431) extols through the support housing(440) from the outer surface (433) to the inner surface (434). The cooling holes (431) include a stadium shape. The stadium shape includes a rectangle with a top and bottom of a first length and ends capped with semicircles with a radius of a second length. The cooling holes (431) are disposed at an angle (98) from thirty to sixty degrees. The angle (98) is between a line (96) projected to the outer surface (433) from an axis of the turbine housing (430) and a line (97) extending through a center of each cooling hole (431) parallel to the first length.

Abstract translation: 涡轮壳体（430）包括具有环形形状的支撑壳体（440）。 支撑壳体（432）包括外表面（433）和内表面（434）。 内表面（434）从外表面（433）径向向内定位。 多个冷却孔（431）从外表面（433）向内表面（434）伸出支撑壳体（440）。 冷却孔（431）包括体育场形状。 体育场形状包括具有第一长度的顶部和底部的矩形，并以半径为第二长度的半圆封口。 冷却孔（431）以三十到六十度的角度（98°）设置。 角度（98）在从涡轮机壳体（430）的轴线突出到外表面（433）的线（96）和延伸穿过平行于所述涡轮机壳体（430）的每个冷却孔（431）的中心的线（97）之间 第一长。