公开(公告)号：US20070240415A1

公开(公告)日：2007-10-18

申请号：US11208648

申请日：2005-08-23

Applicant: Andre Julien ,  Andre Chevrefils

Inventor： Andre Julien ,  Andre Chevrefils

IPC: F02G3/00 ,  F16P7/00

CPC classification number: F02C6/12 ,  F02C3/055 ,  F02C3/08 ,  F02C3/107 ,  F02C5/06 ,  Y02T50/671

Abstract: A compound cycle engine (10) comprises a compressor and a turbine section (14, 18), and at least one cycle topping device (16) providing an energy input to the turbine section (18). The compressor section (14) compresses the air according to a pressure ratio PRgt. The cycle topping device (16) further compresses the air according to a volumetric compression ratio Rvc, and wherein PRgt×Rvc are selected, according to one aspect of the invention, to provide a cycle which permit a more compact and lighter compound cycle engine to be provided.

Abstract translation: 复合循环发动机（10）包括压缩机和涡轮部分（14,18），以及至少一个提供到涡轮部分（18）的能量输入的循环顶部装置（16）。 压缩机部分14根据压力比PR＆gt;压缩空气。 循环顶部装置（16）进一步根据体积压缩比R vc而压缩空气，并且其中选择PR <！ - SIPO

公开(公告)号：US6155056A

公开(公告)日：2000-12-05

申请号：US90209

申请日：1998-06-04

Applicant: Parthasarathy Sampath ,  Andre Chevrefils ,  Denis Leclair ,  Robert Desroches

Inventor： Parthasarathy Sampath ,  Andre Chevrefils ,  Denis Leclair ,  Robert Desroches

IPC: F02C7/18 ,  F23R3/00 ,  F23R3/10 ,  F23R3/42 ,  F02C1/00

CPC classification number: F23R3/54 ,  F23R3/002 ,  F23R3/10 ,  F05B2260/202 ,  F23R2900/03041

Abstract: The invention provides in a gas turbine engine combustion chamber, an array of elongate louver strips between fuel nozzles of a combustion chamber dome wall, to cool the dome wall and contain combustion gases in the area between nozzles. The elongate louver strips are each disposed symmetrically along the median line on the inner surface dome wall and extend between each nozzle cup of the annular array. Each strip includes an elongate flange extending into the combustion chamber from the inner dome wall. The flange has an inner surface, and lateral side walls, with the inner surface generally parallel to the inner surface of the dome wall. Compressed air outlets are disposed along each flange lateral side wall, for directing a compressed air film along the inner surface of the dome wall in a direction away from the median line. A compressed air inlet extends from the outer surface of the dome wall to the outlets.

Abstract translation: 本发明在燃气涡轮发动机燃烧室中提供在燃烧室圆顶壁的燃料喷嘴之间的细长百叶条的阵列，以冷却圆顶壁并且在喷嘴之间的区域中容纳燃烧气体。 细长百叶条各自沿着内表面圆顶壁上的中线对称设置并且在环形阵列的每个喷嘴杯之间延伸。 每个条带包括从内圆顶壁延伸进入燃烧室的细长凸缘。 凸缘具有内表面和侧壁，内表面大致平行于圆顶壁的内表面。 压缩空气出口沿着每个凸缘侧壁设置，用于沿着远离中线的方向沿圆顶壁的内表面引导压缩空气膜。 压缩空气入口从圆顶壁的外表面延伸到出口。

公开(公告)号：US06832893B2

公开(公告)日：2004-12-21

申请号：US10278899

申请日：2002-10-24

Applicant: Andre Chevrefils ,  Que Dan Pham

Inventor： Andre Chevrefils ,  Que Dan Pham

IPC: F01D508

CPC classification number: F01D5/081 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/22141

Abstract: A passively cooled blade platform for a gas turbine rotor adapted for rotation about an axis within a stationary coolant fluid. The platform has a radially outer surface defining an annular gas path, a radially inner surface in flow communication with the coolant fluid, a leading edge, and a trailing edge. The inner surface includes at least one cooling flow channel in the inner surface. Each channel has a flow path from a channel inlet to a channel outlet, preferably with a tangential component at the inlet opposite to the direction of rotation and an axial component at the outlet. The flow channels are defined by ribs or pedestals extending radially inwardly from the platform inner surface to direct cooling fluid flow and create turbulence to dissipate heat from the platform on exposure to cooling fluid flow.

Abstract translation: 用于燃气轮机转子的被动冷却的叶片平台，其适于围绕固定的冷却剂流体内的轴线旋转。 平台具有限定环形气体路径的径向外表面，与冷却剂流体，前缘和后缘流动连通的径向内表面。 内表面包括在内表面中的至少一个冷却流道。 每个通道具有从通道入口到通道出口的流动路径，优选地在与入口方向相反的入口处的切向部件和出口处的轴向部件。 流动通道由从平台内表面径向向内延伸的肋或基座限定，以引导冷却流体流动并且在暴露于冷却流体流动时产生湍流以从平台散发热量。