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公开(公告)号：US10782054B2
公开(公告)日：2020-09-22
申请号：US15902648
申请日：2018-02-22
Inventor： Daniel G. Edwards , Eric E. Wilson
IPC: F01P3/00 , F25B45/00 , F25B17/02 , B60H1/00 , F25B41/06 , F25D3/00 , F28D20/00 , F25B25/00 , F25D17/02 , F25D16/00 , F02B29/04
Abstract: A cooling system may include a cooling pump, a cooling source, a thermal energy storage, a mixing valve, a recharge valve, a recharge pump. The mixing valve may be in fluid communication with a thermal load. A first input of the mixing valve may be in fluid communication with the thermal energy storage. A second input of the mixing valve may be in fluid communication with the recharge pump. Operation of the recharge pump may cause heated cooling fluid output from the thermal load to bypass the cooling pump and flow to the second input of the mixing valve. The recharge valve may be in fluid communication with the thermal energy storage and the cooling pump. The recharge valve may regulate a recharge fluid flow comprising cooling fluid received from the thermal energy storage.
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公开(公告)号：US10778126B2
公开(公告)日：2020-09-15
申请号：US16297654
申请日：2019-03-09
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Mark Jon Blackwelder , Paul M. Rancuret
Abstract: A system includes one or more synchronous generators and one or more corresponding exciters. The exciter is configured to output a field current for exciting the synchronous generator to produce a voltage and a current at an output of the synchronous generator. The system may also include one or more electric motors electrically coupled to the synchronous generator and configured to drive one or more mechanical loads. A controller included in the system is configured to identify power angle oscillations between the voltage and the current and control an exciter voltage of the exciter to damp the identified power angle oscillations.
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公开(公告)号：US10778125B2
公开(公告)日：2020-09-15
申请号：US16667886
申请日：2019-10-29
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Mark Jon Blackwelder , Paul M. Rancuret
Abstract: A system includes a synchronous generator coupled to an excitation system. The excitation system may output an excitation signal to excite the synchronous generator to produce a voltage and a current at an output of the synchronous generator. During startup, when the synchronous generator is rotating at less than rated speed, non-rotating synchronous electric motors may be electrically coupled to the synchronous generator. A controller may direct the excitation system to output the excitation signal to generate, with the synchronous generator, a first magnitude of current flow, and the synchronous motor loads are non-rotational in response to receipt of the first magnitude of current flow. In addition, the controller may selectively direct output of a pulse of the excitation signal, when the synchronous generator is rotating at less than rated speed, to urge the non-rotating synchronous motor loads into rotational electrical alignment with the synchronous generator and each other.
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公开(公告)号：US20200277871A1
公开(公告)日：2020-09-03
申请号：US16510184
申请日：2019-07-12
Inventor： Jun Shi , Matthew R. Gold
IPC: F01D11/12
Abstract: In some examples, a component includes a substrate and a non-continuous abradable coating on the substrate. The abradable coating includes a first portion defining a first plurality of coating blocks, a second portion defining a second plurality of coating blocks, and a blade rub portion extending between the first portion and the second portion and defining a third plurality of coating blocks. At least one of the first plurality of coating blocks or the second plurality of coating blocks is different than the third plurality of coating blocks in at least one coating block parameter.
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公开(公告)号：US20200271060A1
公开(公告)日：2020-08-27
申请号：US16281995
申请日：2019-02-21
Inventor： Christopher Hall , William Barry Bryan
Abstract: A system and method for meeting take off noise requirements in a gas turbine engine with a multi-stage fan, comprising an inlet passage, a core passage, a bypass passage and a mid-stage offtake passage; the core passage comprising a core inlet, high pressure compressor, combustor, high pressure turbine, low pressure turbine and a core exhaust; the bypass passage comprising a primary bypass inlet and a primary bypass exit; the mid-stage offtake passage comprising an offtake inlet and offtake exit; a first stage comprising a first rotor, and a second stage comprising a second rotor; and a variable guide vane located axially between the first rotor and the second rotor; an actuator coupled to and selectively varying the variable guide vane between two or more orientations; a variable offtake exit thrust nozzle; and, wherein a gas stream exiting the inlet passage enters one of the core, bypass or mid-stage off take passages as a function of the two or more orientations.
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Patent Agency Ranking
公开(公告)号：US20200271000A1
公开(公告)日：2020-08-27
申请号：US16870773
申请日：2020-05-08
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Mark O'Leary
IPC: F01D5/18
Abstract: A method of manufacturing a gas turbine engine component and said resulting component configuration are disclosed. The method includes providing a ceramic structure including a sacrificial ceramic core. The ceramic structure is inserted into a casting mold. A component material is introduced into the casting mold. The ceramic structure is removed after the component material has solidified to define a casted component having a cooling cavity of a heat exchanger segment formed in the wall structure of the component. The ceramic body of the sacrificial ceramic core defines a plurality of apertures and includes a trailing first pin and a leading first pin. The trailing first pin and the leading first pin are extended away from an inner surface of the body, and the leading first pin is spaced from the trailing first pin and in closer proximity to a leading edge of the body than the trailing first pin.
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公开(公告)号：US20200266741A1
公开(公告)日：2020-08-20
申请号：US16691427
申请日：2019-11-21
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Keith D. Noderer
Abstract: A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.
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公开(公告)号：US10738636B2
公开(公告)日：2020-08-11
申请号：US15378915
申请日：2016-12-14
Inventor： Mark O'Leary
Abstract: An airfoil adapted for use in a gas turbine engine is disclosed herein. The airfoil includes a spar defining an interior space and a cover sheet extending around at least a portion of the spar. The cover sheet is bonded to the spar to define a cooling cavity between the spar and the cover sheet.
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公开(公告)号：US20200248710A1
公开(公告)日：2020-08-06
申请号：US16714220
申请日：2019-12-13
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Edward C. Rice
IPC: F04D29/32 , F04D29/28 , F04D29/30 , F04D29/02 , F04D29/38 , F04D29/62 , F04D29/64 , F01D5/30 , F01D5/34
Abstract: A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.
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公开(公告)号：US10731481B2
公开(公告)日：2020-08-04
申请号：US15340663
申请日：2016-11-01
Inventor： Daniel K. Vetters , Ted J. Freeman , James Glen Schwefel , Phil Bastnagel
Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.
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