公开(公告)号：DE602005020229D1

公开(公告)日：2010-05-12

申请号：DE602005020229

申请日：2005-10-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ALBERT JASON E ,  PIETRASZKIEWICZ EDWARD F

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/14

Abstract: A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which, together with an impingement rib (35), defines a fillet cavity (24) therebetween, and cooling air is provided to flow through impingement holes (26) in the impingement rib (3 5) and impinge on the rear surface (27) of the fillet (18). The impingement holes (26) are elongated in cross sectional shape with their elongations being oriented in a direction generally transverse to a radial direction.

公开(公告)号：SG143163A1

公开(公告)日：2008-06-27

申请号：SG2007176399

申请日：2007-11-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHLICHTING KEVIN W ,  LITTON DAVID A ,  PIETRASZKIEWICZ EDWARD F ,  FRELING MELVIN ,  DIERBERGER JAMES A

Abstract: THERMAL BARRIER COATING FOR COMBUSTOR PANELS A method is disclosed that selectively applies thermal barrier coatings that exhibit different degrees of thermal conductivity to different inner surface areas of engine combustor panels. Different types of TBCs are applied to predetermined inner surface areas of a combustor panel based on empirical observation or prediction. TBCs exhibiting low thermal conductivity are applied to combustor panel areas that are exposed to hotter temperatures and TBCs exhibiting higher thermal conductivity are applied to areas that are exposed to lower temperatures.

公开(公告)号：SG135099A1

公开(公告)日：2007-09-28

申请号：SG2007007198

申请日：2007-01-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PIETRASZKIEWICZ EDWARD F ,  CHIN KAR D ,  SHARMA OM P

Abstract: A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the cooling channel. The pressure drop results from the cross-sectional area of the pre-meter orifice being less than the cross-sectional area of the adjacent cooling channel. After flowing through the cooling channel, the cooling air exits the cooling channel through a film hole to form a film layer over the airfoil to cool and insulate the turbine blade.

公开(公告)号：SG130131A1

公开(公告)日：2007-03-20

申请号：SG2006053581

申请日：2006-08-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK ,  SHARMA OM PARKASH ,  PIETRASZKIEWICZ EDWARD F

Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.

公开(公告)号：SG130124A1

公开(公告)日：2007-03-20

申请号：SG2006053292

申请日：2006-08-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK ,  SHARMA OM PARKASH ,  PIETRASZKIEWICZ EDWARD F

Abstract: A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.

公开(公告)号：AU2006203730A1

公开(公告)日：2007-03-15

申请号：AU2006203730

申请日：2006-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SILVERMAN RICHARD ,  BECKWITH BARRY ,  O'NEILL LISA ,  PIETRASZKIEWICZ EDWARD F

IPC: F01D5/08 ,  F01D5/00 ,  F01D25/12

Abstract: A gas turbine engine (120) is provided with a radially outer cooling air flow (26). A dirt separator (130) is placed in the path of the radially outer cooling air flow (26), and includes a radially outer leg (134) that defines a space (133) to capture dirt or other impurities. A radially inner leg (135) of the dirt separator (130) includes open air flow passages (136) to allow air to flow through the inner leg (135) and downstream to cool various components within the gas turbine engine (120).

公开(公告)号：CA2558479A1

公开(公告)日：2007-02-28

申请号：CA2558479

申请日：2006-08-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHARMA OM PARKASH ,  PIETRASZKIEWICZ EDWARD F ,  CUNHA FRANK

IPC: B22F5/04 ,  F01D5/18 ,  F01D5/28

Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.

公开(公告)号：SG122883A1

公开(公告)日：2006-06-29

申请号：SG200506801

申请日：2005-10-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PIETRASZKIEWICZ EDWARD F ,  BOTNICK CHRISTINA ,  COONS TODD

Abstract: A turbine blade airfoil assembly (12) includes a cooling air passage (30). The cooling air passage (30) includes a plurality of impingement openings (32) that are isolated from at least one adjacent impingement opening (32). The cooling air passage (30) is formed and cast within a turbine blade assembly through the use of a single core (44). The single core (44) forms the features required to fabricate the various separate and isolated impingement openings (32). The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

公开(公告)号：SG121991A1

公开(公告)日：2006-05-26

申请号：SG200506678

申请日：2005-10-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ALBERT JASON E ,  PIETRASZKIEWICZ EDWARD F

Abstract: A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which, together with an impingement rib (35), defines a fillet cavity (24) therebetween, and cooling air is provided to flow through impingement holes (26) in the impingement rib (3 5) and impinge on the rear surface (27) of the fillet (18). The impingement holes (26) are elongated in cross sectional shape with their elongations being oriented in a direction generally transverse to a radial direction.

公开(公告)号：EP2971539A4

公开(公告)日：2016-06-22

申请号：EP13866646

申请日：2013-12-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOONANKEIL JAMES M ,  PIETRASZKIEWICZ EDWARD F ,  SCHACHTNER KARL A ,  KLINEFELTER KEVIN J ,  FRITCH MARKUS W ,  DALEY JASON

IPC: F01D5/18 ,  B23H9/10 ,  B23H9/14 ,  F01D25/12 ,  F02C7/18

CPC classification number: B23H1/00 ,  B23H7/265 ,  B23H7/30 ,  B23H9/10 ,  F01D5/187 ,  F05D2230/12 ,  F05D2240/12 ,  F05D2240/81 ,  Y02T50/676 ,  Y10T29/49323 ,  Y10T29/49341

Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.