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US09382806B2 Intermediate housing of a gas turbine having an outer bounding wall having a contour that changes in the circumferential direction upstream of a supporting rib to reduce secondary flow losses 有权
具有外围壁的燃气涡轮机的中间壳体具有在支撑肋的上游沿圆周方向变化的轮廓，以减少二次流动损失

  • Patent Title: Intermediate housing of a gas turbine having an outer bounding wall having a contour that changes in the circumferential direction upstream of a supporting rib to reduce secondary flow losses
  • Patent Title (中): 具有外围壁的燃气涡轮机的中间壳体具有在支撑肋的上游沿圆周方向变化的轮廓，以减少二次流动损失
  • Application No.: US13699202
    Application Date: 2012-01-16
  • Publication No.: US09382806B2
    Publication Date: 2016-07-05
  • Inventor: Martin Hoeger , Inga Mahle , Jochen Gier
  • Applicant: Martin Hoeger , Inga Mahle , Jochen Gier
  • Applicant Address: DE Munich
  • Assignee: MTU Aero Engines GmbH
  • Current Assignee: MTU Aero Engines GmbH
  • Current Assignee Address: DE Munich
  • Agency: Davidson, Davidson & Kappel, LLC
  • Priority: DE102011008812 20110119
  • International Application: PCT/DE2012/000032 WO 20120116
  • International Announcement: WO2012/097798 WO 20120726
  • Main IPC: F01D9/02
  • IPC: F01D9/02 ;  F01D25/14 ;  F01D25/24 ;  F01D5/14
Intermediate housing of a gas turbine having an outer bounding wall having a contour that changes in the circumferential direction upstream of a supporting rib to reduce secondary flow losses
Abstract:
Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24′), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24′) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).
Abstract(Chinese):

中间壳体（14），特别是燃气涡轮发动机的涡轮机（11,13），具有径向内部界限壁（23）并且具有径向外侧边界壁（24,24'），具有横流通道 ），其由边界壁（23,24,24'）形成，并且其中至少一个支撑肋（15）被定位成具有前缘（16），后缘（17）以及侧面 在前缘（16）和后缘（17）之间延伸的引导穿过横流通道（33）的气流的壁（18）; 所述径向外边界壁（24）具有至少在所述支撑肋（15）上游的一个部分中在圆周方向上变化的轮廓。

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