公开(公告)号：US20050232762A1

公开(公告)日：2005-10-20

申请号：US10829114

申请日：2004-04-20

申请人： Jason Smoke ,  Cristopher Frost ,  Richard Kocher ,  Jeff Guymon ,  Ly Nguyen

发明人： Jason Smoke ,  Cristopher Frost ,  Richard Kocher ,  Jeff Guymon ,  Ly Nguyen

IPC分类号： F01D9/02 ,  F04D29/44 ,  F04D29/62

CPC分类号： F04D29/444 ,  F01D9/026 ,  F04D29/624 ,  F05D2220/40 ,  F05D2250/52

摘要： A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.

摘要翻译： 一种与涡轮机械结合使用的压缩机涡旋壳体，特别适用于飞机。 涡旋壳体可以包括围绕涡旋壳体排列的多个涡旋叶片。 与涡旋壳体一体形成的涡旋叶片在涡旋壳体上承受应力负荷，包括来自涡卷内的流体压力的负载和来自发动机的胎体负载。 多个涡旋叶片适于在支撑涡旋壳体的同时引导流体从入口到出口的流动。 每个涡旋叶片的弦长和横截面面积的尺寸可以确保在所有涡旋叶片中保持相等的应力。 公开了一种制造与连接到发动机的叶轮一起使用的涡旋壳体的方法，以及一种操作涡轮机械的方法，包括在涡轮叶片上支撑负载，同时在每个涡旋叶片上保持相等的应力。

公开(公告)号：US20050212283A1

公开(公告)日：2005-09-29

申请号：US10810456

申请日：2004-03-26

申请人： Cristopher Frost ,  Richard Kocher

发明人： Cristopher Frost ,  Richard Kocher

IPC分类号： F16L19/02 ,  F16L19/025 ,  F16L55/00

CPC分类号： F16L27/1008 ,  F02C7/00 ,  F16L19/02 ,  F16L19/0212 ,  F16L19/025 ,  Y02T50/671 ,  Y10S285/917

摘要： A low profile tension style flexible joint for pneumatic ducting may be useful as, for example, a joint for aircraft engine pneumatic ducting. The joint of the present invention may be used at both ends of a duct that passes high temperature (up to about 1200° F.) and high pressure (up to about 110 psia) compressor air to the combustor of a turbomachine. Some turbomachines, such as the turbo engine of a jet-powered aircraft, require a very short curved duct to fit into an unusually small aircraft installation envelope. Moreover, these installations also require those features found in conventional flex joints, including being able to support the axial load inherent in pressurized ducting systems. Unlike conventional flexible joints, such as ball joints, gimble joints and pressure compensated joints, the low profile tension style flexible joint of the present invention provides a low profile, low weight design with the ability to support the axial load inherent in pressurized ducting systems.

摘要翻译： 用于气动管道的低轮廓张力式柔性接头可用作例如飞机发动机气动管道的接头。 本发明的接头可以在通过高温（高达约1200°F）和高压（高达约110psia）的压缩机空气到涡轮机的燃烧器的管道的两端使用。 一些涡轮机，例如喷气式飞机的涡轮发动机，需要非常短的弯曲管道，以适应非常小的飞机安装外壳。 此外，这些安装还需要在传统的挠性接头中发现的特征，包括能够支撑加压管道系统中固有的轴向载荷。 与传统的柔性接头（例如球形接头，柔性接头和压力补偿接头）不同，本发明的低轮廓张力型柔性接头提供了低外形，低重量的设计，具有支撑加压管道系统固有的轴向载荷的能力。

公开(公告)号：US20050056019A1

公开(公告)日：2005-03-17

申请号：US10666611

申请日：2003-09-17

申请人： Ly Nguyen ,  Cristopher Frost ,  Ronald Maty ,  John Wait ,  Jason Smoke ,  Lori Wheeler ,  Richard Kocher

发明人： Ly Nguyen ,  Cristopher Frost ,  Ronald Maty ,  John Wait ,  Jason Smoke ,  Lori Wheeler ,  Richard Kocher

IPC分类号： F02C6/08 ,  F02C7/00 ,  F02C7/04 ,  F02C7/26

CPC分类号： F02C7/20 ,  F02C7/06 ,  F04D29/4206 ,  F05D2230/52 ,  Y02T50/672

摘要： A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.

摘要翻译： 利用多部件集成的涡轮发动机压缩机设计，从而减少所需发动机部件的数量。 在传统的压缩机设计中，多分量系统使得在瞬态条件下难以预测由于热和机械负载引起的结构行为。 本发明的压缩机设计具有三个主要部分：前进轴承壳体，喇叭口（隔热罩）和耦合叶轮罩/扩散器。 这样的设计实现了本发明的设计目标，包括减轻重量，降低成本，最小化公差建立，并通过利用多种发动机运行模式的多部件集成来改善空气动力性能。