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111.发明专利
公开(公告)号：CA2853839A1
公开(公告)日：2013-08-08
申请号：CA2853839
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , SUCIU GABRIEL L , KUPRATIS DANIEL BERNARD , ACKERMANN WILLIAM K
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. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.
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公开(公告)号：CA1225334A
公开(公告)日：1987-08-11
申请号：CA497631
申请日：1985-12-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BROWN WAYNE M , NEAL WILLIAM F , SCHWARZ FREDERICK M
Abstract: Rotor Thrust Bearing A turbine construction in which the axial loading on the rotor including the compressor and turbine resulting from cooling air pressure in the compartment between the compressor and turbine is balanced by making the compressor and turbine areas exposed to the cooling air of equal area as by having the seals at compressor and turbine ends of the compartment equal in radius with respect to the air of the rotor.
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公开(公告)号：DE3542584A1
公开(公告)日：1986-06-19
申请号：DE3542584
申请日：1985-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , GRIFFIN JAMES G
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公开(公告)号：CA1180562A
公开(公告)日：1985-01-08
申请号：CA383559
申请日：1981-08-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , GRIFFIN JAMES G
Abstract: A structure and method for providing cooling fluids from a compression section to a turbine section of an axially flow rotary machine is disclosed. Various construction details and steps of the method enable the machine to minimize the effect that unscheduled variations in the temperature of the cooling fluids have on operating clearances in the turbine section. These unscheduled variations may result from changes in ambient temperature and component deterioration. An internal cooling fluid from the discharge region of the rearmost compressor is used to modulate the flow of a second fluid impinged on the exterior of the outer case for controlling the clearance between an array of rotor blades and a coolable stator shroud spaced radially outwardly of the rotor blades. In one embodiment, a valve for modulating the flow of the second fluid has at least one thermostatic bimetallic spring for transducing a change in temperature into a displacement. The displacement changes the flow area Af between a valve head and a conical seat in the conduit for the second fluid through the valve.
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公开(公告)号：CA2856723C
公开(公告)日：2021-09-07
申请号：CA2856723
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
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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Patent Agency Ranking
公开(公告)号：CA2898207C
公开(公告)日：2020-03-10
申请号：CA2898207
申请日：2014-02-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , MALECKI ROBERT E
Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.
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公开(公告)号：CA2916866C
公开(公告)日：2020-02-18
申请号：CA2916866
申请日：2016-01-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD
Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.
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公开(公告)号：CA2936576C
公开(公告)日：2018-05-01
申请号：CA2936576
申请日：2016-07-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , PORTLOCK LAWRENCE E , SCHWARZ FREDERICK M
Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).
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公开(公告)号：CA2856912C
公开(公告)日：2017-04-25
申请号：CA2856912
申请日：2013-01-29
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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公开(公告)号：CA2936576A1
公开(公告)日：2017-02-12
申请号：CA2936576
申请日：2016-07-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , PORTLOCK LAWRENCE E , SCHWARZ FREDERICK M
Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).
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