公开(公告)号：JP2006342796A

公开(公告)日：2006-12-21

申请号：JP2006153022

申请日：2006-06-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA

IPC: F01D11/02 ,  F02C7/28 ,  F16J15/44

Abstract: PROBLEM TO BE SOLVED: To provide a seal assembly for restricting leaking-out of cooling air in constant. SOLUTION: An inside cavity 50 is positioned between a vane support part 52 and a rotor assembly 54 on the inside in the radial direction of an annular duct 30. The cooling air 40 is introduced into the cavity 50 by a duct 70, and cools a blade 58 by flowing in a conduit 72. The cavity 50 is separated from the duct 30 by a seal 80 having land 84 and a segment-like ring 86, and air pressure is properly maintained over the whole engine conditions. The ring 86 extends by crossing the cavity 50 from a neck area 96. One complete segment-like ring 86 is formed by aligning a plurality of adjacent ring segments 186 in a state of inserting the blade 58 into a disc. Leaking-out restriction is improved by extending a runner 200 outside in the radial direction from the ring 86 by inclining to a shaft 11. COPYRIGHT: (C)2007,JPO&INPIT

公开(公告)号：JP2006342797A

公开(公告)日：2006-12-21

申请号：JP2006154370

申请日：2006-06-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA ,  VIRTUE JOHN P JR ,  HILL JAMES D ,  PINERO HECTOR M ,  JOHNSON ERIKA

IPC: F01D11/02 ,  F02C7/28

Abstract: PROBLEM TO BE SOLVED: To provide a seal assembly for restricting leaking-out of cooling air in constant. SOLUTION: An inside cavity 50 is positioned between a vane support part 52 and a rotary assembly 54 on the inside in the radial direction of an annular duct 30. The cooling air 40 is introduced into the cavity 50 by a duct 70, and cools a blade 58 by flowing in a conduit 72. The cavity 50 is separated from the duct 30 by a seal 80, and air pressure is properly maintained over the whole engine conditions. A segment-like ring 86 extends by crossing the cavity 50 from a divided rim area 110, and a runner 170 is aligned with land 84. One complete segment-like ring 86 is formed by aligning a plurality of adjacent ring segments 164 and 166 in a state of inserting the blade 58 into a disc. Leaking-out restriction is improved by extending the runner 170 outside or inside in the radial direction from the ring 86 by inclining to a shaft 11. COPYRIGHT: (C)2007,JPO&INPIT

公开(公告)号：CA2564073A1

公开(公告)日：2007-04-27

申请号：CA2564073

申请日：2006-10-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA ,  REINHARDT GREGORY E

IPC: F01D11/08 ,  F01D5/20 ,  F01D25/12

Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

公开(公告)号：DE602005012009D1

公开(公告)日：2009-02-12

申请号：DE602005012009

申请日：2005-03-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALVANOS IOANNIS ,  PINERO HECTOR M ,  AGRAWAL RAJENDRA ,  HU JIN

IPC: F01D5/08 ,  F01D5/18 ,  F01D25/12 ,  F02C7/18

Abstract: A gas turbine engine (20) having a turbine section cooling system is disclosed which is able to cool the turbine section (26) of the g as turbine engine (20) to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils (44), turning holes (54), and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section (26) in a direction in substantial alignment with a gas flow path through the turbine section (26).