公开(公告)号：CA2562434A1

公开(公告)日：2007-05-03

申请号：CA2562434

申请日：2006-10-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CRAIG COLIN D ,  DIBENEDETTO ENZO ,  KMETZ CHRISTOPHER P ,  MILLER JONATHAN L ,  SONDEEN MARK R

IPC: F16J15/34 ,  F02C7/28 ,  F16J15/30

Abstract: A face seal includes a seal seat 24 and a seal element 52 carried by a seal housing 32. The seal element cooperates with the seal seat to establish a seal. The housing includes a support 44 for the seal element and a shroud 42 for effecting a gradual transition between a normal condition and a deteriorated condition. The shroud 42 may have a tip 74 whose properties differ in lubricity, hardness or abradability relative to other portions of the seal housing.

公开(公告)号：DE69920864T2

公开(公告)日：2005-02-03

申请号：DE69920864

申请日：1999-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOVALESKI STANLEY K ,  KOVALESKI DONALD J ,  CRAIG COLIN D

IPC: F02C7/28 ,  F01D11/00 ,  F16J15/44

Abstract: A gas turbine engine (10) includes a plurality of seal stages (50) minimizing leakage of high pressure air from a high pressure cavity (84) into a low pressure cavity (80). The plurality of seal stages (50) includes an upstream seal stage (86), substantially adjacent to the high pressure cavity (84), and a downstream seal stage (90), substantially adjacent to the low pressure cavity (80). Each seal stage (86), includes a seal plate (94,100) and at least one seal (110,108). The downstream seal plate (100) includes a plurality of bleeding holes (136) for metering higher pressure air into the low pressure cavity, thereby balancing a pressure drop between the seal stages. Substantial equalization of the pressure drop among the seal stages reduces wear of the downstream seal (108) and therefore, increases useful life and effectiveness thereof.

公开(公告)号：DE69920864D1

公开(公告)日：2004-11-11

申请号：DE69920864

申请日：1999-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOVALESKI STANLEY K ,  KOVALESKI DONALD J ,  CRAIG COLIN D

IPC: F02C7/28 ,  F01D11/00 ,  F16J15/44

Abstract: A gas turbine engine (10) includes a plurality of seal stages (50) minimizing leakage of high pressure air from a high pressure cavity (84) into a low pressure cavity (80). The plurality of seal stages (50) includes an upstream seal stage (86), substantially adjacent to the high pressure cavity (84), and a downstream seal stage (90), substantially adjacent to the low pressure cavity (80). Each seal stage (86), includes a seal plate (94,100) and at least one seal (110,108). The downstream seal plate (100) includes a plurality of bleeding holes (136) for metering higher pressure air into the low pressure cavity, thereby balancing a pressure drop between the seal stages. Substantial equalization of the pressure drop among the seal stages reduces wear of the downstream seal (108) and therefore, increases useful life and effectiveness thereof.