公开(公告)号：SG107654A1

公开(公告)日：2004-12-29

申请号：SG200302765

申请日：2003-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DILIP M SHAH ,  JAMES T BEALS ,  NORMAN PIETRUSKA ,  EDWARD R SZELA

IPC: B23P6/04 ,  B23K9/04 ,  B23K10/02 ,  B23K37/06 ,  B23P6/00 ,  C23C28/00 ,  F01D5/00 ,  F01D5/28 ,  F02C7/00 ,  B23K26/34 ,  F01D5/18

Abstract: The present invention relates to a method for repairing components such as blades used in turbine engines. The method comprises the steps of placing a piece of refractory metal material (16) over an area of the component to be repaired (12) and depositing a repair filler metal material (20) over the piece of refractory material (16) in an amount sufficient to repair the component and welding the repair filler metal material (20) in place. The refractory metal material (16) may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof and may be uncoated or coated.

公开(公告)号：SG10201603121UA

公开(公告)日：2016-11-29

申请号：SG10201603121U

申请日：2016-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LIM YUAN KWANG ,  CHEE YAO HUI ,  ZHENG CHUAN CHEN ,  CHARLENE KWAN YEE LING ,  MARIO P BOCHIECHIO ,  AWADH B PANDEY ,  DILIP M SHAH

Abstract: A pour liner for a shot sleeve of a die-casting system including a bonding layer within a slot in a shot sleeve substrate and a refractory metal layer adjacent to the bonding layer. A method of manufacturing a shot sleeve including forming a slot in the slot sleeve, laser cladding a bonding layer within the slot, and laser cladding a refractory metal layer onto the bonding layer.

公开(公告)号：SG108232A1

公开(公告)日：2005-01-28

申请号：SG200007303

申请日：2000-12-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM PATRICK ALLEN ,  WALTER E OLSON ,  DILIP M SHAH ,  ALAN DAVID CETEL

IPC: C22C19/00 ,  C23C4/00 ,  C23C4/08 ,  C23C30/00 ,  F01D5/28 ,  C23C10/52

Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.

公开(公告)号：SG111971A1

公开(公告)日：2005-06-29

申请号：SG200206371

申请日：2002-10-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DILIP M SHAH ,  JAMES THOMPSON BEALS ,  JOHN JOSEPH MARCIN JR ,  STEPHEN DOUGLAS MURRAY

IPC: B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  B22C21/14 ,  B22D29/00

Abstract: Concepts for fabricating improved cores for investment casting are described. The cores are composite and include refractory metal elements (200,202,204,206,208,210,212,214,216) and ceramic elements (120). The refractory metal elements are provided to enhance the mechanical properties of the core and/or to permit the fabrication of cores having shapes and geometries that could not otherwise be achieved. In one embodiment, the entire core may be made of refractory metal components. The cores may be used to investment cast gas turbine superalloy components.

公开(公告)号：SG103377A1

公开(公告)日：2004-04-29

申请号：SG200207404

申请日：2002-12-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： READE CLEMENS ,  DILIP M SHAH ,  DAVID LEE ROE

IPC: B25H7/04 ,  B44B3/06 ,  B26B3/00

公开(公告)号：SG180155A1

公开(公告)日：2012-05-30

申请号：SG2011081452

申请日：2011-11-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MARIO P BOCHIECHIO ,  DILIP M SHAH ,  LEA KENNARD CASTLE ,  DOUGLAS M BERCZIK ,  JOHN JOSEPH MARCIN ,  CARL R VERNER

Abstract: An example die casting system includes a die comprised of a plurality of diecomponents that define a die cavity configured to receive a molten metal. One of the die components comprises a material that is not reactive with the molten metal and has a melting temperature above 815 degrees Celsius.Figure 1

公开(公告)号：UA73989C2

公开(公告)日：2005-10-17

申请号：UA20021210223

申请日：2002-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALAN D SETEL ,  DILIP M SHAH

IPC: F02C7/00 ,  C22C19/05

Abstract: The invention relates to the non-ferrous metallurgy and concerns high-strength, corrosion resistant alloy resistant to oxidation, and also the components made thereof. The components are made of alloy containing, % by weight: chrome 10 û 13.5, cobalt 8 - 10, molybdenum 1,25 - 2,5, tungsten 3.25 û 4.25, tantalum 4.5 û 6, aluminium 3.25 û 4.5, titanium 3 û 4.75, boron 0.0025 û 0.025, carbon 0.05 û 0.15, and nickel is the rest. The obtained components have a good resistance to the high temperature corrosion and increased properties relative to creeping and resistance to oxidation.

公开(公告)号：SG96589A1

公开(公告)日：2003-06-16

申请号：SG200007299

申请日：2000-12-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM PATRICK ALLEN ,  WALTER E OLSON ,  DILIP M SHAH ,  ALAN DAVID CETEL

IPC: C23C4/00 ,  C23C30/00 ,  F01D5/28 ,  B32B15/00 ,  C22C19/00 ,  C23C16/00

Abstract: According to the invention, an article that is exposed to high temperature e.g., over 1000° C. during operation is disclosed. In one embodiment, a method for a gas turbine engine includes a directionally solidifed metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY or a noble metal containing aluminide or corrosion inhibiting ceramic is located on portions or the blade not previously covered with such coatings, e.g., the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also created, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.

公开(公告)号：SG114762A1

公开(公告)日：2005-09-28

申请号：SG200501174

申请日：2005-03-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DILIP M SHAH ,  ALAN D CETEL ,  ALAN W STONER ,  WILLIAM P ALLEN

IPC: C22C19/05 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

Abstract: A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life.

公开(公告)号：SG111239A1

公开(公告)日：2005-05-30

申请号：SG200406155

申请日：2004-10-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JAMES T BEALS ,  DILIP M SHAH ,  JACOB SNYDER ,  JOHN WIEDEMER

IPC: B22C1/00 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24