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公开(公告)号：JPH10195564A
公开(公告)日：1998-07-28
申请号：JP34742997
申请日：1997-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MALLEY DAVID R
Abstract: PROBLEM TO BE SOLVED: To provide the machined surface of a nickel superalloy which is not damaged in the process of machining by the conventional tungsten carbide, in which the nickel superalloy article with a finished shape dimension has excellent low cycle fatigue strength and suitable for the structural parts of a gas turbine engine. SOLUTION: This high strength nickel superalloy article having a machined surface is the one having a compsn. contg., by weight. 1.2 to 3.5% Al, 3.0 to 7.0% Ti, 12.0 to 20.0% Cr, 2.0 to 3.9% Mo, 10.0 to 20.0% Co, 0 to 4.5% W, 0.005 to 0.025% C, 0.005 to 0.05% B, 0.01 to 0.1% Zr, 0 to 0.005% Mg, 0 to 1.0% Ta, 0 to 1.0% Nb, 0 to 2.0% Fe, 0 to 0.3% Hf, 0 to 0.02% Y, 0 to 0.1% V, 0 to 1.0% Re, and the balance substantial Ni. This superalloy contains plural discrete carbides substantially contg. no molybdenum for increasing its fatigue strength.
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公开(公告)号：DE602007000708D1
公开(公告)日：2009-04-30
申请号：DE602007000708
申请日：2007-06-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MALLEY DAVID R
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公开(公告)号：NO165930C
公开(公告)日：1991-05-02
申请号：NO845117
申请日：1984-12-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PAULONIS DANIEL F , MALLEY DAVID R , BROWN EDGAR E
Abstract: Forging processes are described for cast superalloys. The forgeability of superalloy materials is improved by the development of overaged microstructure. The total forging process is usually performed in a series of steps with intervening heat treatments to reform the overaged microstructure.
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公开(公告)号：DE602007010700D1
公开(公告)日：2011-01-05
申请号：DE602007010700
申请日：2007-07-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MALLEY DAVID R , RUTZ DAVID A , MOOR JAMES J
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公开(公告)号：GB2151951B
公开(公告)日：1987-03-25
申请号：GB8431277
申请日：1984-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PAULONIS DANIEL F , MALLEY DAVID R , BROWN EDGAR E
Abstract: Forging processes are described for cast superalloys. The forgeability of superalloy materials is improved by the development of overaged microstructure. The total forging process is usually performed in a series of steps with intervening heat treatments to reform the overaged microstructure.
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Patent Agency Ranking
公开(公告)号：DE3445768A1
公开(公告)日：1985-07-04
申请号：DE3445768
申请日：1984-12-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PAULONIS DANIEL F , MALLEY DAVID R , BROWN EDGAR E
Abstract: Forging processes are described for cast superalloys. The forgeability of superalloy materials is improved by the development of overaged microstructure. The total forging process is usually performed in a series of steps with intervening heat treatments to reform the overaged microstructure.
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公开(公告)号：IT8424262D0
公开(公告)日：1984-12-27
申请号：IT2426284
申请日：1984-12-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PAULONIS DANIEL F , MALLEY DAVID R , BROWN EDGARD E
Abstract: Forging processes are described for cast superalloys. The forgeability of superalloy materials is improved by the development of overaged microstructure. The total forging process is usually performed in a series of steps with intervening heat treatments to reform the overaged microstructure.
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公开(公告)号：CA1097006A
公开(公告)日：1981-03-10
申请号：CA305410
申请日：1978-06-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ANDERSON DAVID W , KING WILLIAM H , MALLEY DAVID R
Abstract: A fusion welded surfacing process for use with crack prone substrates is described. The process involves the application of an intermediate layer of crack resistant alloy by fusion welding followed by the application of the desired final surfacing alloy by fusion welding. The intermediate layer is an age hardenable nickel superalloy to which intentional additions of manganese have been mate. The final surfacing alloy may be of the hardfacing type or may be of a type which imparts corrosion and oxidation resistance to the underlying article.
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公开(公告)号：MXPA06014621A
公开(公告)日：2008-10-15
申请号：MXPA06014621
申请日：2006-12-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KINSTLER MONIKA D , MULLOOLY JOHN F , ROSE WILLIAM M , MALLEY DAVID R
IPC: F01D5/00
Abstract: La presente invención describe un método para reparar un componente de motor de turbina. El método comprende ampliamente las etapas de proporcionar un componente de motor de turbina que tiene una porción de superficie aerodinámica, aplicar un revestimiento a la porción de superficie aerodinámica y restaurar una porción de punta, una cuerda y superficies de la porción de superficie aerodinámica a sus dimensiones originales en una sola operación. También describe un sistema para reparar el componente de motor de turbina.
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公开(公告)号：DE602005007831D1
公开(公告)日：2008-08-14
申请号：DE602005007831
申请日：2005-10-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： IVORY STEVEN , ECHEVARRIA JOSE A , MCMAHON KEVIN C , LOMASNEY GARY L , MALLEY DAVID R , MOOR JAMES J , ROKICKI JOSEPH
IPC: B23K1/00 , B23K1/018 , B23K1/20 , B23P6/04 , C23G1/08 , F01D5/00 , F01D5/22 , F01D5/30 , F01D9/04
Abstract: A method of repairing a braze joint (16) and the resulting joint includes removing an unsuitable portion (20) of a first joining material (18) in a joint (16) between a first member (12) and a second member (14) of an aerospace assembly (10) and cleaning the joint (16). A stripping solution is used to remove the unsuitable portion (20) of the first joining material (18). A first cleaning solution is used to clean the joint (16), and the joint (16) is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material (60) moves into a void left by the removed unsuitable portion (20) from the removal step to form a new joint between the first member (12) and the second member (14) that includes the remaining first joining material (18) and the second joining material (60).
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