中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

62 records (took 0.04 seconds)

    Thrust reverser for aerial vehicle
    1.
    发明授权
    Thrust reverser for aerial vehicle 有权

    公开(公告)号：US12071911B1

    公开(公告)日：2024-08-27

    申请号：US18327961

    申请日：2023-06-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad

    IPC: F02K1/60

    CPC classification number: F02K1/605

    Abstract: A thrust reverser for an aerial vehicle is coupled to an engine associated with the aerial vehicle. The thrust reverser includes a housing configured to receive an exhaust flow. The housing is movable relative to the aerial vehicle between at least a first, stowed position and a second, deployed position. The housing includes at least one inner flange that defines a first curvature. The thrust reverser includes a pair of doors coupled to the housing. The pair of doors is movable between at least a first position and a second position based on a movement of the housing. Each door of the pair of doors includes a leading edge and a trailing edge. The trailing edge is downstream from the leading edge in a direction of the exhaust flow through the housing, and the leading edge has a second curvature that is substantially the same as the first curvature.

    TRANSLATING COWL THRUST REVERSER PRIMARY LOCK SYSTEM
    2.
    发明公开
    TRANSLATING COWL THRUST REVERSER PRIMARY LOCK SYSTEM 审中-公开

    公开(公告)号：US20230228230A1

    公开(公告)日：2023-07-20

    申请号：US17648305

    申请日：2022-01-19

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad

    IPC: F02K1/76 ,  F02K1/72

    CPC classification number: F02K1/766 ,  F02K1/763 ,  F02K1/72 ,  F05D2220/323 ,  F05D2260/31 ,  F05D2260/52 ,  F05D2260/57

    Abstract: A primary lock system for a translating cowl thrust reverser system includes a primary lock having a housing, a lock, and a manual mechanism. The lock is disposed at least partially within, and is movable relative to, the housing and is movable between a lock position and an unlock position. The manual mechanism is coupled to the lock and is configured, in response to a manual input force supplied to the manual mechanism, to: selectively move from a first position to a second position, whereby the lock is selectively moved from the lock position to the unlock position, respectively, and selectively prevent movement of the lock out of the lock position.

    SYSTEMS FOR SOUND ATTENUATION
    3.
    发明申请
    SYSTEMS FOR SOUND ATTENUATION 有权

    公开(公告)号：US20230033240A1

    公开(公告)日：2023-02-02

    申请号：US17443492

    申请日：2021-07-27

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad

    IPC: F02C7/24 ,  G10K11/16

    Abstract: A sound attenuating cell includes a first sound attenuating cavity defined between a first sidewall and a second sidewall. The first sidewall is opposite the second sidewall. The first sidewall includes a first undulating surface and the second sidewall includes a second undulating surface. A deflector is coupled to the first undulating surface. The deflector extends from the first undulating surface toward the second undulating surface. The first undulating surface is axially offset from the second undulating surface to define a tortuous path between the first sidewall and the second sidewall. The first sound attenuating cavity has a first end and a second end. The first end is opposite the second end, and an inlet and an outlet of the first sound attenuating cavity is defined at the first end. The sound attenuating cell includes a second sound attenuating cavity nested within the first sound attenuating cavity.

    COMPACT ACCESSORY SYSTEMS FOR A GAS TURBINE ENGINE
    6.
    发明申请
    COMPACT ACCESSORY SYSTEMS FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180372004A1

    公开(公告)日：2018-12-27

    申请号：US16057507

    申请日：2018-08-07

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad ,  Tomasz Dobosz ,  Rocio Chavez

    IPC: F02C7/32 ,  F16H1/22 ,  B64D41/00 ,  F02C3/04 ,  B64C27/14

    Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft. A first accessory axis of rotation and a second accessory axis of rotation are substantially transverse to the shaft axis of rotation.

    Shielded anti-icing system and methods
    7.
    发明授权
    Shielded anti-icing system and methods 有权

    公开(公告)号：US09950799B2

    公开(公告)日：2018-04-24

    申请号：US15064748

    申请日：2016-03-09

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Morris Anderson ,  Shawn Alstad

    IPC: B64D15/04

    CPC classification number: B64D15/04 ,  B64D2033/0233 ,  F02C6/06 ,  F02C7/047

    Abstract: An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.

    TRANSLATING COWL THRUST REVERSER WITH DOOR PIVOTS AFT OF REVERSE FLOW PATH
    9.
    发明申请
    TRANSLATING COWL THRUST REVERSER WITH DOOR PIVOTS AFT OF REVERSE FLOW PATH 审中-公开
    翻转车轮倒车者与门面转弯逆行道路

    公开(公告)号：US20160305370A1

    公开(公告)日：2016-10-20

    申请号：US14688779

    申请日：2015-04-16

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Danis Burton Smith ,  Mark Knowles ,  Robert Romano ,  Shawn Alstad ,  David Robinson ,  Israel Picazo

    IPC: F02K1/60 ,  F02K1/72

    CPC classification number: F02K1/605 ,  F02K1/72 ,  Y02T50/671

    Abstract: A thrust reverser system capable of providing high efficiency within a tightly constrained nacelle is provided. The thrust reverser system provides a displaceable internal door pivotally mounted within a transcowl. The displaceable internal door is rotatable about a pivot axis that is positioned aft of a front edge of the transcowl when the transcowl is in a deployed position.

    Abstract translation: 提供了能够在紧密限制的机舱内提供高效率的推力反向器系统。 推力反向器系统提供可枢转地安装在转子内的可移动内门。 可移动的内部门可以围绕枢转轴线旋转，当枢轴转动器处于展开位置时，该枢转轴线定位在转子的前边缘的后方。

    NACELLE INLET AND ENGINE FAN HOUSING ASSEMBLY AND METHOD FOR MAKING SAME
    10.
    发明申请
    NACELLE INLET AND ENGINE FAN HOUSING ASSEMBLY AND METHOD FOR MAKING SAME 审中-公开
    NACELLE入口和发动机风扇壳体组件及其制造方法

    公开(公告)号：US20160084108A1

    公开(公告)日：2016-03-24

    申请号：US14494868

    申请日：2014-09-24

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Justin C. Mickelsen ,  Shawn Alstad ,  Mark Knowles ,  Bill Russell Watson

    IPC: F01D25/04 ,  F01D25/24

    CPC classification number: F01D25/04 ,  F01D25/24 ,  F02C7/045 ,  F05D2220/36 ,  F05D2230/53 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2260/96

    Abstract: A system and method is provided for coupling a nacelle inlet assembly to an engine fan housing structure that provides adequate clearance and access for removing a blisk fan from a turbofan engine. This is accomplished by utilizing a nacelle inlet forward compartment, referred to herein as the “D-lip”and an acoustic liner that are inseparable and removable as an integral unit, providing sufficient clearance for removable of the blisk fan. The nacelle inlet assembly may be slidably coupled to the engine fan housing structure, minimizing assembly interfaces and therefore overall aircraft engine weight.

    Abstract translation: 提供了一种用于将机舱入口组件耦合到发动机风扇壳体结构的系统和方法，该发动机风扇壳体结构提供足够的间隙和通路以从涡轮风扇发动机移除叶轮风扇。 这是通过利用这里称为“D唇”的机舱前进舱和作为整体单元不可分离和可拆卸的声学衬垫来实现的，为空挡风扇提供足够的间隙。 机舱入口组件可以可滑动地联接到发动机风扇壳体结构，使组装界面最小化，从而使整个飞机发动机重量最小化。

Patent Agency Ranking