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公开(公告)号：DE69107988D1
公开(公告)日：1995-04-13
申请号：DE69107988
申请日：1991-12-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , CANDELORI DAVID J , BROOKE RICHARD D
Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the vane (52) between the turbines (42, 48) from a plenum (24). A modulatable valve in the supply line to the plenum (24) regulates the air flow in response to a gas temperature sensed in the seal area by a thermocouple (26). Valve and thermocouples are checked for proper operation. Immediate alerts and maintenance messages are established along with fail safe operating conditions upon fault detection. Over cooling of the seal area during low power operation, in anticipation of a power increase, is used to improve low cycle fatigue life of the turbine disk and seal runner.
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公开(公告)号：ES2695074T3
公开(公告)日：2018-12-28
申请号：ES12198045
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , PORTLOCK LAWRENCE E , SCHWARZ FREDERICK M
Abstract: Un motor (10) de turbina que comprende: un árbol (20) de ventilador; un ventilador (18); y un tren (22) de engranajes epicicloidales acoplado para accionar el ventilador (18), incluyendo el tren (22) de engranajes epicicloidales un portador (26), que soportan engranajes (32) intermedios que engranan con un engranaje (30) solar, y un engranaje (38) de anillo que rodea y engrana con los engranajes (32) intermedios, caracterizado por que: cada uno de los engranajes (32) intermedios es soportado sobre un cojinete (34) de apoyo; el tren (22) de engranajes epicicloidales define una relación de reducción de engranaje de más de o igual a 2,5; el motor (10) comprende además al menos un cojinete (80) cónico montado sobre el árbol (20) de ventilador; el árbol (20) de ventilador incluye al menos un paso (82) que se extiende radialmente adyacente al menos a un cojinete (80) cónico; al menos un cojinete (80) cónico incluye un primer cojinete (80a) cónico y un segundo cojinete (80b), de rodillo cónico axialmente Espaciado, y al menos un paso (82) que se extiende radialmente incluye: un primer paso (82a) y un segundo paso (82b), estando ubicado el primer paso (82a) en un lado axialmente hacia adelante del primer cojinete (80a) cónico y estando ubicado el segundo paso (82b) en un lado axialmente hacia atrás del primer cojinete (80a) cónico; y un tercer paso y un cuarto paso, estando ubicado el tercer paso en un lado axialmente hacia delante del segundo cojinete (80b) cónico y estando ubicado el cuarto paso en un lado axialmente hacia atrás del segundo cojinete (80b) cónico; y el ventilador (18) tiene una relación de presión que es menor que 1,45 durante la operación y es montado para rotación sobre el cojinete (80) cónico.
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公开(公告)号：CA2923326C
公开(公告)日：2018-05-29
申请号：CA2923326
申请日：2016-03-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , HASEL KARL L
IPC: F02C7/36
Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000 °F and about 1500 °F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.
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公开(公告)号：CA2884976C
公开(公告)日：2018-03-06
申请号：CA2884976
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOMZER DAVID , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.
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公开(公告)号：CA2857357C
公开(公告)日：2017-06-06
申请号：CA2857357
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.
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Patent Agency Ranking
公开(公告)号：CA2856561C
公开(公告)日：2017-05-30
申请号：CA2856561
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GARIEL L , SCHWARZ FREDERICK M , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：CA2933432A1
公开(公告)日：2017-01-01
申请号：CA2933432
申请日：2016-06-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC: F02C7/36
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：BR102016000128A2
公开(公告)日：2016-10-04
申请号：BR102016000128
申请日：2016-01-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: turbina de motor de turbina a gás, e, motor uma turbina de motor de turbina a gás tem uma turbina de alta pressão configurada para girar com um compressor de alta pressão como um carretel de alta pressão numa primeira direção em torno de um eixo central e uma turbina de baixa pressão configurada para girar com um compressor de baixa pressão como um carretel de baixa pressão na primeira direção em torno do eixo central. uma densidade de energia é maior ou igual a cerca de 1,5 e menor ou igual a cerca de 5,5 lbf/polegadas cúbicas. um ventilador é conectado ao carretel de baixa pressão via um mecanismo de mudança de velocidade e gira na primeira direção.
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公开(公告)号：CA2923331A1
公开(公告)日：2016-09-19
申请号：CA2923331
申请日：2016-03-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC: F02C7/36
Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.
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公开(公告)号：CA2857351C
公开(公告)日：2016-06-28
申请号：CA2857351
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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