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公开(公告)号：US12116940B2
公开(公告)日：2024-10-15
申请号：US17215575
申请日：2021-03-29
CPC分类号： F02C9/20 , F02K3/04 , F04D27/0246 , F05D2270/023 , F05D2270/052 , F05D2270/053 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/335 , F05D2270/71
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
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公开(公告)号：US11555453B2
公开(公告)日：2023-01-17
申请号：US17368317
申请日：2021-07-06
发明人： Keith Morgan , Robert Peluso , Ghislain Plante , Eugene Gekht , Eric Durocher , Jean Dubreuil
IPC分类号： F02C7/32 , F02C3/14 , F02C6/20 , F02C3/04 , F02C3/067 , F02C3/113 , F02C7/36 , F01D1/26 , F04D25/02
摘要： A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
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公开(公告)号：US10533559B2
公开(公告)日：2020-01-14
申请号：US15384655
申请日：2016-12-20
发明人： Ghislain Plante , Patrick Valois
IPC分类号： F02C3/14 , F04D25/04 , F04D19/02 , F04D29/053 , F04D27/00 , F04D29/32 , F01D5/06 , F01D15/12 , F04D29/58 , F01D9/02
摘要： A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.
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公开(公告)号：US20160032733A1
公开(公告)日：2016-02-04
申请号：US14448615
申请日：2014-07-31
发明人： Ghislain Plante
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2270/114
摘要： A turbine blade comprises an airfoil. An outer shroud at a tip of the airfoil, has a main surface facing the airfoil and forming a first plateau. A gusset or gussets have a periphery raising from the main surface, and a second plateau between the periphery and the airfoil. A gas turbine engine with such turbine blade is also provided.
摘要翻译： 涡轮机叶片包括翼型件。 在翼型的尖端处的外护罩具有面向翼型的主表面并形成第一平台。 角撑板或角撑板具有从主表面升起的周边，以及在周边和翼面之间的第二平台。 还提供了具有这种涡轮叶片的燃气涡轮发动机。
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公开(公告)号：US11994034B2
公开(公告)日：2024-05-28
申请号：US16157476
申请日：2018-10-11
发明人： Ghislain Plante , Ian MacFarlane
CPC分类号： F01D17/105 , F01D21/006 , F02C3/13 , F02C3/145 , F02C6/08 , F02C9/18 , F02K3/075 , F05D2220/3217 , F05D2220/3219 , F05D2260/4023 , F05D2260/606 , F05D2260/902
摘要： A low pressure compressor section of a gas turbine engine includes low pressure compressor stages spaced apart along an axis of rotation of the low pressure compressor section. The low pressure compressor section includes at least one of a fluid conduit extending between an air inlet of the gas turbine engine and the low pressure compression stages. The fluid conduit having at least one flow diverter displaceable between a first position and a second position to modulate air through the low pressure compressor stages. And/or a compressor stage disabler is engageable with at least one of the low pressure compressor stages and configured to reduce a rotation thereof.
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公开(公告)号：US11578663B2
公开(公告)日：2023-02-14
申请号：US16565736
申请日：2019-09-10
发明人： Ghislain Plante , Keith Morgan , Stephen Mah , Patrick Valois , Robert Peluso
摘要： A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.
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公开(公告)号：US11125239B2
公开(公告)日：2021-09-21
申请号：US16717268
申请日：2019-12-17
发明人： Ghislain Plante , Patrick Valois
IPC分类号： F02C3/14 , F04D25/04 , F04D19/02 , F04D29/053 , F04D27/00 , F04D29/32 , F01D5/06 , F01D15/12 , F04D29/58 , F01D9/02 , F02C7/36 , F02C7/143 , F02K3/06
摘要： A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.
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公开(公告)号：US10598023B2
公开(公告)日：2020-03-24
申请号：US15693936
申请日：2017-09-01
摘要： A power turbine includes a second stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
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公开(公告)号：US10221695B2
公开(公告)日：2019-03-05
申请号：US15170110
申请日：2016-06-01
发明人： Michael Papple , Ghislain Plante
摘要： A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil. The serpentine passage has at least three segment serially interconnected in fluid flow communication. The leading edge cooling passage and the serpentine cooling passage have separate coolant inlets. The coolant inlet of the serpentine passage comprises a primary inlet branch connected in fluid flow communication with a first one of the segments of the serpentine passage and a secondary inlet branch connected in flow communication with a last one of the segments, thereby providing for a portion of the flow passing through the coolant inlet of the serpentine passage to be directly fed into the last segment of the serpentine passage.
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公开(公告)号：US10808624B2
公开(公告)日：2020-10-20
申请号：US15428572
申请日：2017-02-09
IPC分类号： F02C7/32 , B64D27/10 , F02C3/107 , F02C7/36 , F01D15/10 , F01D15/12 , F04D29/32 , F04D29/053 , F02C3/10 , F02C6/20 , F01D15/00 , F02C3/14
摘要： A method and a turbine rotor system for reducing over-speed potential of a turbine of a gas turbine engine involve mechanically connecting the turbine to at least two mechanical loads via first and second mechanical drives extending in opposite directions from the turbine.
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