公开(公告)号：AT424963T

公开(公告)日：2009-03-15

申请号：AT05253843

申请日：2005-06-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUDSON ERIC A ,  HARDING BENJAMIN R

IPC: B23P15/04 ,  F01D5/18

Abstract: A cooled turbine engine component is made by providing first and second pieces (46,44) respectively having first and second surfaces (64,68). At least one circuit (100) is formed in at least one of the first and second surfaces (68). A first plurality of apertures (114) is provided in the first piece (46) to form inlets to the at least one circuit (100). A second plurality of apertures (140) is provided in the second piece (44) to form outlets to the at least one circuit (100). A combination of the first and second pieces is assembled and integrated.

公开(公告)号：DE602005019002D1

公开(公告)日：2010-03-11

申请号：DE602005019002

申请日：2005-06-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HARDING BENJAMIN R ,  HUDSON ERIC A

IPC: F01D5/18

Abstract: A vane assembly (10) suitable for a turbine engine features a refractory vane (12) with an internal cavity (20) and a pair of flexible metallic baffles (26) extending into the cavity (20) from spanwisely opposite ends of the vane (12). A rigid fastener (40), such as a nut and bolt assembly applies a tensile load to the baffles (26). The tensile load is reacted out as a compressive load applied to the vane (12). In another embodiment, the baffle (26) is relatively rigid but the fastener (52) is flexible. The compressive loading exerted on the vane (12) counteracts the brittleness customarily exhibited by refractory materials and imparts damage tolerance to the vane (12). The arrangement also allows the use of a metal baffle (26) that can be easily secured to the vane (12) and dispenses with any need for a potentially troublesome seal between the baffles and the spanwise extremities of the vane (12).