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公开(公告)号：US10731559B2
公开(公告)日：2020-08-04
申请号：US15875179
申请日：2018-01-19
Applicant: United Technologies Corporation
IPC: F01D25/18 , F02C7/06 , F01D25/20 , F02C7/14 , F01M1/16 , F16H57/04 , F02C3/107 , F02C7/36 , F01M13/04
Abstract: A lubrication system for a gas turbine engine according to an example of the present disclosure includes, among other things, a pump that moves a lubricant, a lubricant tank that stores the lubricant, a first engine component and a second engine component each requiring lubrication from the lubricant, a conduit between the lubricant tank and the first engine component and between the lubricant tank and the second engine component, a scheduling valve positioned in the conduit between the lubricant tank, and the first engine component and the second engine component, and a controller including a memory and a processor that controls the scheduling valve, wherein the memory includes an engine performance model, wherein the engine performance model includes stored relationship values between more than one condition experienced by the gas turbine engine during operation and a position of the scheduling valve, and wherein the scheduling valve varies a flow of the lubricant to the first engine component, the second engine component and the lubrication tank based on comparing the more than one condition with the engine performance model.
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公开(公告)号：US20180327117A1
公开(公告)日：2018-11-15
申请号：US16034550
申请日：2018-07-13
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, JR. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, JR. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.
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公开(公告)号：US20180265223A1
公开(公告)日：2018-09-20
申请号：US15985782
申请日：2018-05-22
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, JR. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, JR. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
CPC classification number: B64F1/34 , B64D27/16 , F02C7/27 , F02C7/277 , F05D2220/323 , F05D2260/85 , F05D2270/303 , F05D2270/71
Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.
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公开(公告)号：US10023319B2
公开(公告)日：2018-07-17
申请号：US15258197
申请日：2016-09-07
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Stewart B. Hatch , Wyatt S. Daentl
IPC: G06F19/00 , B64D31/06 , F04D27/00 , F04D29/32 , F04D25/04 , F01D5/02 , F01D17/10 , F01D17/14 , F01D17/16 , B64D27/10
Abstract: A control system for a gas turbine engine includes a processing system operable to control a speed of the gas turbine engine and a memory system. The memory system is operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally adjust an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit according to the at least one performance parameter.
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公开(公告)号：US09874145B2
公开(公告)日：2018-01-23
申请号：US14697223
申请日：2015-04-27
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F02C7/06 , F01D25/20 , F01M1/16 , F01M2013/0472 , F02C3/107 , F02C7/14 , F02C7/36 , F05D2260/53 , F16H57/0435 , F16N2250/08 , Y02T50/671
Abstract: A lubrication system for a gas turbine engine may include a pump for moving a lubricant through a conduit from a lubricant tank to an engine component. Further, a scheduling valve positioned in the conduit between the lubricant tank and the engine component may vary a flow of the lubricant to the engine component based on a condition.
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Patent Agency Ranking
公开(公告)号：US10830140B2
公开(公告)日：2020-11-10
申请号：US15875279
申请日：2018-01-19
Applicant: United Technologies Corporation
Abstract: A method of controlling lubrication flow to a first engine component, a second engine component and a lubrication tank of a gas turbine engine according to an example of the present disclosure includes, among other things, determining more than one condition experienced by the gas turbine engine, comparing with a processor on a controller the more than one condition against an engine performance model stored in memory on the controller, wherein the engine performance model includes stored relationship values between the more than one condition and a position of a scheduling valve, the scheduling valve disposed between the lubricant tank and the first engine component and between the lubricant tank and the second engine component, pumping a lubricant from the lubricant tank through a conduit to the scheduling valve using a pump, and controlling the position of the scheduling valve to vary a flow of the lubricant to two or more of the first engine component, the second engine component and the lubrication tank based upon the comparing of the more than one condition experienced by the gas turbine engine.
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公开(公告)号：US10787277B2
公开(公告)日：2020-09-29
申请号：US16034550
申请日：2018-07-13
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, Jr. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, Jr. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.
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公开(公告)号：US09878799B2
公开(公告)日：2018-01-30
申请号：US15112648
申请日：2014-10-03
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Ethan K. Stearns
CPC classification number: B64D37/34 , B64D27/10 , F02C7/06 , F02C7/14 , F02C7/22 , F02C7/224 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/20 , F05D2270/313 , Y02T50/675
Abstract: A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.
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公开(公告)号：US20160312699A1
公开(公告)日：2016-10-27
申请号：US14697223
申请日：2015-04-27
Applicant: United Technologies Corporation
CPC classification number: F02C7/06 , F01D25/20 , F01M1/16 , F01M2013/0472 , F02C3/107 , F02C7/14 , F02C7/36 , F05D2260/53 , F16H57/0435 , F16N2250/08 , Y02T50/671
Abstract: A lubrication system for a gas turbine engine may include a pump for moving a lubricant through a conduit from a lubricant tank to an engine component. Further, a scheduling valve positioned in the conduit between the lubricant tank and the engine component may vary a flow of the lubricant to the engine component based on a condition.
Abstract translation: 用于燃气涡轮发动机的润滑系统可以包括用于将润滑剂通过导管从润滑剂罐移动到发动机部件的泵。 此外，位于润滑剂罐和发动机部件之间的导管中的调度阀可以基于条件改变润滑剂与发动机部件的流动。
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公开(公告)号：US10267326B2
公开(公告)日：2019-04-23
申请号：US13669510
申请日：2012-11-06
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Paul H. Spiesman , Kerri A. Wojcik , John R. Gendron , Glenn D. Bartkowski , Sean D J Blake , William G. Tempelman
Abstract: An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling flow through a compressor of a turbomachine includes moving variable vanes to positions that allow more flow into the compressor in response to bleed air being communicated away from the compressor.
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