公开(公告)号：EP2900920A4

公开(公告)日：2016-07-06

申请号：EP13853442

申请日：2013-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRAISNER THOMAS J ,  AGGARWALA ANDREW S ,  NASH TIMOTHY CHARLES ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A

IPC: F01D5/14 ,  F04D29/68

CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D5/145 ,  F04D29/324 ,  F04D29/542 ,  F04D29/681 ,  Y02T50/673

公开(公告)号：EP2847449A4

公开(公告)日：2015-12-02

申请号：EP13787820

申请日：2013-05-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GROVER ERIC A ,  PRAISNER THOMAS J ,  WAGNER JOEL H

IPC: F02C7/28 ,  F01D5/08 ,  F01D11/00 ,  F01D11/10 ,  F01D25/00 ,  F02D7/00

CPC classification number: F01D11/001 ,  F01D5/081 ,  F01D11/02 ,  F05D2250/73 ,  F05D2260/97

公开(公告)号：EP2809886A4

公开(公告)日：2015-10-07

申请号：EP12867672

申请日：2012-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRAISNER THOMAS J ,  MAGGE SHANKAR S ,  ESTES MATTHEW B

IPC: F01D9/04 ,  F01D5/14 ,  F01D9/06 ,  F02C3/04

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D9/04 ,  F01D9/065 ,  F01D25/28 ,  F02K3/06 ,  F05D2240/12 ,  Y02T50/673

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A mid turbine frame is arranged axially between the first and second stages. The mid turbine frame includes a circumferential array of airfoils, and the airfoils each have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°, for example. In one example, an airfoil aspect ratio is less than 1.5.

公开(公告)号：EP3090143A4

公开(公告)日：2017-12-06

申请号：EP14869239

申请日：2014-11-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LEWIS SCOTT D ,  KOHLI ATUL ,  PRAISNER THOMAS J

IPC: F01D5/14 ,  F01D11/00

CPC classification number: F01D11/08 ,  F01D5/12 ,  F01D5/143 ,  F01D9/02 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/80 ,  F05D2250/192 ,  F05D2250/231

Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.

公开(公告)号：EP3084137A4

公开(公告)日：2017-01-25

申请号：EP14887328

申请日：2014-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHAKKA PITCHAIAH VIJAY ,  AGGARWALA ANDREW S ,  PRAISNER THOMAS J ,  SPANGLER BRANDON W

IPC: F01D5/14

CPC classification number: F01D25/12 ,  F01D5/12 ,  F01D5/145 ,  F01D9/02 ,  F02C3/04 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

公开(公告)号：EP2844861A4

公开(公告)日：2015-05-06

申请号：EP13784265

申请日：2013-04-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  PRAISNER THOMAS J

IPC: F02K3/04

CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2260/40311

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.