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公开(公告)号：US20170107943A1
公开(公告)日：2017-04-20
申请号：US14886466
申请日：2015-10-19
Applicant: General Electric Company
Inventor： Matthew Timothy Franer , Brandon Wayne Miller
CPC classification number: F02K1/72 , F01D25/24 , F02C3/04 , F02K1/09 , F02K1/763 , F04D19/002 , F04D29/522 , F05D2220/32 , F05D2220/36 , Y02T50/672
Abstract: A turbofan engine is provided having a fan and a core in flow communication with the fan. The turbofan engine also includes a nacelle assembly enclosing the fan and at least a portion of the core to define a bypass passage with the core. The nacelle assembly includes a fan cowl extending around the fan and a thrust reverser system. The thrust reverser system is movable between a fully stowed position, a partially deployed position, and a fully deployed position. The thrust reverser system is configured to be held in the partially deployed position to allow an additional amount of airflow to exit from the bypass passage.
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Patent Agency Ranking
公开(公告)号：US20170167438A1
公开(公告)日：2017-06-15
申请号：US14966007
申请日：2015-12-11
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Matthew Timothy Franer , Alan Roy Stuart
CPC classification number: F02K1/70 , F01D5/02 , F01D5/12 , F01D15/12 , F01D25/16 , F01D25/24 , F02C7/04 , F02K1/06 , F02K1/72 , F02K3/06 , F05D2220/36 , F05D2250/10 , F05D2250/42
Abstract: A gas turbine engine includes a fan and a core in flow communication with the fan. The core includes an aftmost turbine, and the aftmost turbine includes an aftmost stage of rotor blades. The gas turbine engine also includes a nacelle assembly having a translating and rotating thrust reverser system and enclosing the fan and at least a portion of the core. The nacelle assembly defines a nacelle assembly length between a forward lip and an aft edge. Additionally, the gas turbine engine defines an engine length between the forward lip of the nacelle assembly and the aftmost stage of rotor blades of the aftmost turbine. A ratio of the turbine length to the nacelle assembly length is greater than about 0.5 and less than about 1.
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公开(公告)号：US20250019071A1
公开(公告)日：2025-01-16
申请号：US18515830
申请日：2023-11-21
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorski , Matthew Timothy Franer
Abstract: An aircraft defining a vertical direction, a longitudinal direction, and a transverse direction is provided. The aircraft includes: a fuselage; a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage in the transverse direction. The wing includes a support structure that comprises a plurality of first support members and a plurality of second support members. The plurality of first support members extending at least partially between the plurality of second support members. The plurality of vertical thrust electric fans arranged between the plurality of first support members and the plurality of second support members.
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公开(公告)号：US10378479B2
公开(公告)日：2019-08-13
申请号：US14886466
申请日：2015-10-19
Applicant: General Electric Company
Inventor： Matthew Timothy Franer , Brandon Wayne Miller
Abstract: A turbofan engine is provided having a fan and a core in flow communication with the fan. The turbofan engine also includes a nacelle assembly enclosing the fan and at least a portion of the core to define a bypass passage with the core. The nacelle assembly includes a fan cowl extending around the fan and a thrust reverser system. The thrust reverser system is movable between a fully stowed position, a partially deployed position, and a fully deployed position. The thrust reverser system is configured to be held in the partially deployed position to allow an additional amount of airflow to exit from the bypass passage.
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公开(公告)号：US09677424B2
公开(公告)日：2017-06-13
申请号：US14748368
申请日：2015-06-24
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Matthew Timothy Franer , Kyle Robert Snow
CPC classification number: F01D25/22 , B01D45/16 , F01D5/02 , F01D15/08 , F01D25/18 , F02C7/06 , F04D29/321 , F05D2220/32 , F05D2240/60 , F05D2260/609 , F05D2260/98
Abstract: A gas turbine engine is provided defining a radial direction. The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath. The gas turbine engine also includes a sump positioned inward of the core air flowpath along the radial direction. An air pump is positioned inward of the core air flowpath along the radial direction for providing a flow of air from the sump to lower an internal pressure of the sump and reduce a likelihood of lubrication leaking from the sump.
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公开(公告)号：US20170145956A1
公开(公告)日：2017-05-25
申请号：US14946933
申请日：2015-11-20
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Matthew Timothy Franer , Manxue Lu
CPC classification number: F02K1/763 , F02C3/04 , F02K1/72 , F02K1/76 , F05D2220/32 , F05D2270/051 , F05D2270/304
Abstract: A method for controlling a gas turbine engine includes receiving, with a controller, a thrust reverse command to activate a thrust reverse feature of the gas turbine engine. The method also includes determining the thrust reverse feature is in a starting position, confirming a gas turbine engine condition is at a first value, and moving the thrust reverse feature to a middle position. The method also includes confirming the gas turbine engine condition is at a second value in coordination with moving the thrust reverse feature to the middle position. Additionally, after moving the thrust reverse feature to the middle position and confirming the gas turbine engine condition is that a second value in coordination with such movement, the method includes moving the thrust reverse feature to a maximum position.
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