公开(公告)号：US20050109039A1

公开(公告)日：2005-05-26

申请号：US10722977

申请日：2003-11-26

Applicant: Abdullatif Chehab ,  David Little

Inventor： Abdullatif Chehab ,  David Little

IPC: F01D11/24 ,  F02C7/00

CPC classification number: F01D11/24

Abstract: Aspects of the invention relate to a turbine engine system and method for actively managing blade tip clearances during part load operation of the engine. Aspects of the invention relate to extracting a portion of the combustion gases from the combustor section of the engine and routing these heated gases to the blade rings or other stationary structure surrounding the turbine blades. Upon exposure to the combustion gases, which can be mixed with compressor exit air, the stationary structure will thermally expand, causing blade tip clearances to increase. Thus, concerns of blade tip rubbing are minimized. Once the engines achieves steady state operation, the flow of the combustion gases to the blade rings can be substantially restricted so that only compressor exit air is supplied to the stationary structure. Consequently, the stationary structure will contract and the blade tip clearances will decrease, thereby increasing the efficiency of the turbine.

Abstract translation: 本发明的方面涉及一种用于在发动机的部分负载运行期间主动地管理叶片顶端间隙的涡轮发动机系统和方法。 本发明的方面涉及从发动机的燃烧器部分提取一部分燃烧气体并且将这些加热的气体引导到围绕涡轮机叶片的叶片环或其它静止结构。 当暴露于可与压缩机出口空气混合的燃烧气体时，固定结构将热膨胀，导致叶片尖端间隙增大。 因此，叶片尖端摩擦的问题被最小化。 一旦发动机达到稳态运行，燃烧气体到叶片环的流动可以被大体上限制，使得只有压缩机出口空气被供应到固定结构。 因此，固定结构将收缩并且叶片顶端间隙将减小，从而提高涡轮机的效率。

公开(公告)号：US07086233B2

公开(公告)日：2006-08-08

申请号：US10722977

申请日：2003-11-26

Applicant: Abdullatif Chehab ,  David A. Little

Inventor： Abdullatif Chehab ,  David A. Little

IPC: F02C1/00

CPC classification number: F01D11/24

Abstract: Aspects of the invention relate to a turbine engine system and method for actively managing blade tip clearances during part load operation of the engine. Aspects of the invention relate to extracting a portion of the combustion gases from the combustor section of the engine and routing these heated gases to the blade rings or other stationary structure surrounding the turbine blades. Upon exposure to the combustion gases, which can be mixed with compressor exit air, the stationary structure will thermally expand, causing blade tip clearances to increase. Thus, concerns of blade tip rubbing are minimized. Once the engines achieves steady state operation, the flow of the combustion gases to the blade rings can be substantially restricted so that only compressor exit air is supplied to the stationary structure. Consequently, the stationary structure will contract and the blade tip clearances will decrease, thereby increasing the efficiency of the turbine.

Abstract translation: 本发明的方面涉及一种用于在发动机的部分负载运行期间主动地管理叶片顶端间隙的涡轮发动机系统和方法。 本发明的方面涉及从发动机的燃烧器部分提取一部分燃烧气体并且将这些加热的气体引导到围绕涡轮机叶片的叶片环或其它静止结构。 当暴露于可与压缩机出口空气混合的燃烧气体时，固定结构将热膨胀，导致叶片尖端间隙增大。 因此，叶片尖端摩擦的问题被最小化。 一旦发动机达到稳态运行，燃烧气体到叶片环的流动可以被大体上限制，使得只有压缩机出口空气被供应到固定结构。 因此，固定结构将收缩并且叶片顶端间隙将减小，从而提高涡轮机的效率。