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公开(公告)号：US12123305B2
公开(公告)日：2024-10-22
申请号：US17993517
申请日：2022-11-23
CPC分类号： F01D11/003 , F01D5/025 , F01D5/30 , F05D2220/32 , F05D2240/20 , F05D2240/55
摘要： A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal, and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：US12085022B2
公开(公告)日：2024-09-10
申请号：US16835813
申请日：2020-03-31
发明人： Daniel Alecu , Ninad Joshi
摘要： A fluid system of an aircraft engine includes a first and second fluid conduits. The first conduit fluid conduit fluidly connects to the aircraft engine. A pump fluidly connects to the first fluid conduit and moves therethrough a fluid imparting an excitation frequency to the fluid. The second fluid conduit fluidly connects to the first fluid conduit and to a pressure sensor. A weight is disposed in the second fluid conduit and movable between a first and second positions. A mass of the weight and a liquid capacitance of the second fluid conduit between the second position and a second end of the second fluid conduit define a resonance frequency that is less than the excitation frequency. Fluid pressure monitoring and pressure noise filter construction methods are also disclosed.
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公开(公告)号：US12065972B2
公开(公告)日：2024-08-20
申请号：US18092637
申请日：2023-01-03
发明人： Daniel Alecu , David Menheere
IPC分类号： F02C7/28 , F01D9/06 , F01D25/12 , F01D25/18 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16
CPC分类号： F02C7/28 , F01D9/065 , F01D25/125 , F01D25/183 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2240/60 , F05D2260/221
摘要： Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.
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公开(公告)号：US20240227050A9
公开(公告)日：2024-07-11
申请号：US17971108
申请日：2022-10-21
发明人： Daniel Alecu , Laslo T. Diosady
摘要： A system for forming a nozzle inlet of a nozzle includes a nozzle body and an electro-chemical machining (ECM) assembly. The nozzle body includes an external surface. The nozzle body forms a nozzle orifice and a manifold passage. The nozzle orifice extends through the nozzle body between and to a nozzle inlet and a nozzle outlet. The nozzle inlet is disposed at the manifold passage. The nozzle outlet is disposed at the external surface. The ECM assembly is installed on the nozzle body. The ECM assembly includes a machining tool and a flexible line. The machining tool is disposed at the nozzle inlet. The flexible line is attached to the machining tool. The flexible line extends through the nozzle outlet from the machining tool to an exterior of the nozzle body.
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公开(公告)号：US11994080B2
公开(公告)日：2024-05-28
申请号：US17668576
申请日：2022-02-10
发明人： Daniel Alecu
CPC分类号： F02D41/064 , F02C7/06 , F05D2220/323 , F05D2260/98 , F05D2270/303 , F05D2270/44
摘要： A heating system for heating a component in a liquid distribution system of an aircraft engine. The liquid distribution system feeds a liquid to the component. The heating system includes an acoustic generator disposed in communication with the component via a liquid passage of the liquid distribution system. The liquid passage defines a length between the acoustic generator and the component. The acoustic generator generates a resonant frequency selected as a function of the length of the liquid passage to generate a standing wave in the liquid within the liquid passage. The standing wave transmitting energy to the component to heat the component.
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公开(公告)号：US11788433B2
公开(公告)日：2023-10-17
申请号：US17510804
申请日：2021-10-26
发明人： Kenneth Parkman , Daniel Alecu
CPC分类号： F01D25/20 , F01M1/02 , F01M2001/0238 , F01M2250/60
摘要： Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.
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公开(公告)号：US11603796B2
公开(公告)日：2023-03-14
申请号：US17344185
申请日：2021-06-10
发明人： Laslo Diosady , Daniel Alecu
摘要： The auxiliary duct can branch radially outwardly from the bypass duct, have a proximal end fluidly connecting the bypass duct and a distal end, a valve can be activatable to selectively open and close the auxiliary passage, and a structure can protrude partially from the auxiliary duct into the auxiliary passage, the structure spaced apart from the proximal end, between the proximal end and the valve, the structure generating lesser pressure losses when flow in the auxiliary passage is directed towards the distal end than when the flow is directed towards the proximal end.
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公开(公告)号：US11530710B2
公开(公告)日：2022-12-20
申请号：US16774471
申请日：2020-01-28
发明人： Bryan W. Olver , Daniel Alecu , Nick Stina
摘要： An aircraft pneumatic system including a pneumatic actuator arranged to operate at a pressure value at least equal to a pressure threshold, a line fluidly connected between a pneumatic source and the pneumatic actuator, and a venturi disposed upstream of the line and downstream of the pneumatic source. The venturi is configured to receive a source flow from the source at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line corresponds to a source pressure upstream of the venturi, and when the mass flow rate to the venturi is at the graded flow rate value, the line pressure is less than the source pressure.
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公开(公告)号：US11300002B2
公开(公告)日：2022-04-12
申请号：US16707358
申请日：2019-12-09
摘要： A duct for a gas turbine engine, the duct has a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow and a scoop downstream of the opening relative to the direction of the airflow.
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公开(公告)号：US11108302B2
公开(公告)日：2021-08-31
申请号：US16365229
申请日：2019-03-26
发明人： Dana Tomescu , Daniel Alecu
摘要： A machine includes a liquid system and a shaft. The shaft is rotatable about a rotation axis and includes a first part and a second part engaged coaxially with the first part. The first part is rotatable relative to the second part about the rotation axis to define a liquid pump between the first part and the second part. The pump is hydraulically connected to the liquid system. A method of cooling the machine is also provided.
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