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公开(公告)号：US10107378B2
公开(公告)日：2018-10-23
申请号：US14931488
申请日：2015-11-03
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Donald Albert Bradley , Bugra Han Ertas
Abstract: A planet gear train for an engine casing includes a sun gear rotatable by a shaft, a ring gear, a plurality of planet gears rotatably mounted in a planet carrier and meshing with the sun gear and the ring gear, and a damping system. The damping system includes a soft mount disposed about the shaft and coupling the planet carrier the engine casing. The soft mount includes a flexible inner sleeve and a flexible outer sleeve. The flexible inner sleeve and the flexible outer sleeve are fixedly coupled together at respective central portions thereof near the shaft. The damping system further includes a plurality of damping couplers disposed about an outer flange of the planet carrier. The plurality of damping couplers is configured to flexibly couple the flexible inner sleeve to the flexible outer sleeve.
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公开(公告)号：US20180281931A1
公开(公告)日：2018-10-04
申请号：US15475401
申请日：2017-03-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Patrick Michael Marrinan , Paul Robert Gemin , Nicholas Taylor Moore
CPC classification number: B64C21/06 , B64C2230/04 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2221/00 , F01D15/10 , F02K5/00 , F05D2220/36
Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole P = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.
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公开(公告)号：US20180230844A1
公开(公告)日：2018-08-16
申请号：US15429979
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Glenn David Crabtree
Abstract: A propulsion system for an aircraft includes a turbomachine having a first turbine, a primary fan mechanically driven by the first turbine of the turbomachine, and an electric generator mechanically driven by the first turbine of the turbomachine. The propulsion system also includes an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly.
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公开(公告)号：US20180065742A1
公开(公告)日：2018-03-08
申请号：US15259622
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
CPC classification number: B64C29/0033 , B64C21/06 , B64C29/0025 , B64C2230/04 , B64D27/14 , B64D27/20 , B64D27/24 , B64D29/04 , B64D2027/026 , H02K7/1823 , Y02T50/166 , Y02T50/64
Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft.
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公开(公告)号：US20180065740A1
公开(公告)日：2018-03-08
申请号：US15259564
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
CPC classification number: B64C29/0033 , B64D27/12 , B64D27/24 , B64D2027/026 , B64D2221/00
Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
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Patent Agency Ranking
公开(公告)号：US09828862B2
公开(公告)日：2017-11-28
申请号：US14596804
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow , Raymond Anthony Humble
CPC classification number: F01D5/282 , F01D5/147 , F01D21/04 , F01D21/045 , F04D29/324 , Y02T50/672
Abstract: A frangible airfoil that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided, the airfoil having provisions for dissipating energy, self-shredding, and predetermined release trajectory.
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公开(公告)号：US09764848B1
公开(公告)日：2017-09-19
申请号：US15245257
申请日：2016-08-24
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree
CPC classification number: B64D27/18 , B64C11/30 , B64D27/24 , B64D41/00 , B64D2027/026 , B64D2221/00 , F01D15/10 , Y02T50/62
Abstract: A propulsion system for an aircraft includes an electric generator and a turbomachine. The turbomachine is configured to be mounted to a first wing of the aircraft and is operable with the electric generator. The propulsion system additionally includes a first propulsor mechanically coupled to a shaft of the turbomachine and a second propulsor assembly configured to be mounted at a location away from the turbomachine and the first propulsor. The electric generator is in electrical communication with the second propulsor assembly for powering the second propulsor assembly.
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38.发明申请ENGINE ARCHITECTURE WITH REVERSE ROTATION INTEGRAL DRIVE AND VANELESS TURBINE 审中-公开具有反转旋转整体驱动和无级涡轮机的发动机结构公开(公告)号：US20150354502A1
公开(公告)日：2015-12-10
申请号：US14761698
申请日：2014-01-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Craig Miller KUHNE , Christopher Charles GLYNN , Randy M. Vondrell , Andrew BREEZE-STRINGFELLOW , Kurt David MURROW , Darek T. ZATORSKI , Donald Scott YEAGER , Nicholas Rowe DINSMORE , Samuel Jacob MARTIN , Donald Albert BRADLEY
CPC classification number: F02C7/36 , F02C3/073 , F02C3/107 , F02K3/06 , F02K3/072 , F05D2260/4031 , Y02T50/672
Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.
Abstract translation: 燃气涡轮发动机包括风扇，压缩机，具有第一级叶片和第二级叶片的涡轮机，第一级叶片沿第一方向旋转，第二级叶片沿与第一方向相反的第二方向旋转。 第一级叶片彼此直接相邻，与风扇可操作地输入连接的驱动器和与第一级叶片和第二级叶片可操作地输出连接，第一级叶片和第二级叶片驱动风扇通过 驾驶。
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公开(公告)号：US20250146453A1
公开(公告)日：2025-05-08
申请号：US19016281
申请日：2025-01-10
Inventor： Darek Tomasz Zatorski , David Marion Ostdiek , Mohamed Osama , William Joseph Solomon , Brandon Wayne Miller , Randy M. Vondrell , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US20250003375A1
公开(公告)日：2025-01-02
申请号：US18740613
申请日：2024-06-12
Applicant: General Electric Company
Inventor： Joseph George Rose , Thomas Ory Moniz , Tsuguji Nakano , Jeffrey S. Spruill , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, a heat exchanger disposed in the fan duct, and a booster upstream of the heat exchanger, the booster including a booster cowl extending into the fan duct, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet.
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