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    Epicyclic gear system
    2.
    发明授权
    Epicyclic gear system 有权
    行星齿轮系统

    公开(公告)号：US08986160B2

    公开(公告)日：2015-03-24

    申请号：US13718898

    申请日：2012-12-18

    Applicant: Avio S.p.A.

    Inventor： Paolo Altamura ,  Edoardo Curti ,  Giovanni Oddone ,  Michele Gravina ,  Giulio Zagato

    IPC: F16H57/08 ,  F16H1/28

    CPC classification number: F16H1/28 ,  F16H1/2836

    Abstract: In an epicyclic gear system, each planet gear is connected by a respective connecting pin to an asymmetric planet carrier having two plate portions connected to each other, and only one of which is connectable to a reaction member; and at least one end portion of each connecting pin and the plate portion connected to the reaction member are connected by a radially undulated annular wall flexible angularly and radially.

    Abstract translation: 在行星齿轮系统中，每个行星齿轮通过相应的连接销连接到具有彼此连接的两个板部分的不对称行星架上，并且其中仅一个可连接到反作用件; 并且每个连接销的至少一个端部和连接到反作用构件的板部分通过角度和径向柔性的径向波状环形壁连接。

    Inner coating layer for solid-propellant rocket engines
    3.
    发明授权
    Inner coating layer for solid-propellant rocket engines 有权

    公开(公告)号：US11473529B2

    公开(公告)日：2022-10-18

    申请号：US16755060

    申请日：2018-10-11

    Applicant: AVIO S.P.A.

    Inventor： Daniele Schiariti ,  Paolo Bellomi

    IPC: F02K9/34 ,  F02K9/32

    Abstract: An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing agents and plasticizers, from 5% to 7% wt. of aramid fiber and from 10% to 15% wt. of microspheres made of a material selected among glass, quartz and nano clay, having diameter lower than 200 μm, density comprised between 0.30 and 0.34 g/cc and resistance to hydrostatic pressure greater than, or equal to, 4500 psi.

    Forming machine for forming a hollow body, in particular a casing of a solid propellant engine, and deposit head for such a forming machine
    6.
    发明申请
    Forming machine for forming a hollow body, in particular a casing of a solid propellant engine, and deposit head for such a forming machine 审中-公开
    用于形成中空体的成型机，特别是固体推进剂发动机的壳体，以及用于这种成形机的沉积头

    公开(公告)号：US20170044657A1

    公开(公告)日：2017-02-16

    申请号：US15148575

    申请日：2016-05-06

    Applicant: AVIO S.p.A.

    Inventor： Roberto Mastronardi ,  Rosario Rocco Repole ,  Massimiliano Cardelli

    IPC: C23C14/22 ,  F02K9/34

    CPC classification number: B29C70/388 ,  B29C53/66 ,  B29C53/8016 ,  F02K9/34 ,  F05D2230/31 ,  Y10T156/1788

    Abstract: In a machine for forming a hollow body, for example a casing of a solid propellant engine, a tensioned and guided belt comprising a layer of adhesive material and a protective strip is fed from a deposit head, supported by a robot and comprising an unwinding device for unwinding the belt, a winding device for winding the strip, a first pressing roller for pressing the strip and the layer of adhesive material and rotatable about an axis thereof orthogonal to the feed path of the belt and a second pressing roller for pressing the adhesive material and the strip, rotatable about an axis thereof forming an angle other than 90° to the feed path and movable in opposite directions in a direction transversal to feed path.

    Abstract translation: 在用于形成中空体的机器中，例如固体推进剂发动机的壳体，包括粘合剂材料层和保护带的张紧和引导的带从由机器人支撑的沉积头进给，并包括退绕装置 用于卷绕带，用于卷绕带的卷绕装置，用于挤压条带的第一加压辊和粘合剂材料层，并且可绕着与带的进料路径正交的轴线旋转，以及用于挤压粘合剂的第二加压辊 材料和条带，可围绕其轴线旋转，其形成与进给路径不同于90°的角度，并且可沿相反方向在横向于进给路径的方向上移动。

    Epicyclic Gear System
    8.
    发明申请
    Epicyclic Gear System 有权
    行星齿轮系统

    公开(公告)号：US20130184120A1

    公开(公告)日：2013-07-18

    申请号：US13718898

    申请日：2012-12-18

    Applicant: AVIO S.P.A.

    Inventor： Paolo Altamura ,  Edoardo Curti ,  Giovanni Oddone ,  Michele Gravina ,  Giulio Zagato

    IPC: F16H1/28

    CPC classification number: F16H1/28 ,  F16H1/2836

    Abstract: In an epicyclic gear system, each planet gear is connected by a respective connecting pin to an asymmetric planet carrier having two plate portions connected to each other, and only one of which is connectable to a reaction member; and at least one end portion of each connecting pin and the plate portion connected to the reaction member are connected by a radially undulated annular wall flexible angularly and radially.

    Abstract translation: 在行星齿轮系统中，每个行星齿轮通过相应的连接销连接到具有彼此连接的两个板部分的不对称行星架上，并且其中仅一个可连接到反作用件; 并且每个连接销的至少一个端部和连接到反作用构件的板部分通过角度和径向柔性的径向波状环形壁连接。

    METHOD OF PRODUCING AND ASSEMBLING A COOLING DEVICE INSIDE AN AXIAL-FLOW GAS TURBINE BLADE, AND AXIAL-FLOW GAS TURBINE BLADE PRODUCED USING SUCH A METHOD
    9.
    发明申请
    METHOD OF PRODUCING AND ASSEMBLING A COOLING DEVICE INSIDE AN AXIAL-FLOW GAS TURBINE BLADE, AND AXIAL-FLOW GAS TURBINE BLADE PRODUCED USING SUCH A METHOD 审中-公开
    生产和组装轴流式涡轮叶片内的冷却装置的方法和使用这种方法生产的轴流式气体涡轮叶片

    公开(公告)号：US20040109763A1

    公开(公告)日：2004-06-10

    申请号：US10604337

    申请日：2003-07-11

    Applicant: AVIO S.P.A.

    Inventor： Paolo Lorenzo Ciacci ,  Daniele Coutandin ,  Domenico Dalle Crode

    IPC: F01D005/08

    CPC classification number: F01D17/162 ,  F01D5/14 ,  F01D5/189 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A method of producing and assembling a cooling device inside an axial-flow gas turbine blade; the airfoil profile of the blade has an inner surface defining a chamber, and is connected to a supporting structure by two opposite end pins having respective openings for the passage of cooling air and which come out inside the chamber; the method provides for forming an insert having a number of holes and defined by a first and at least a second body separate from each other, and each of a size approximating but no larger than that of at least one of the openings; the bodies are inserted successively through the openings in the pins, and are positioned inside the chamber to direct a relative stream of air through each hole on to the inner surface of the airfoil profile.

    Abstract translation: 一种在轴流式燃气轮机叶片内制造和组装冷却装置的方法; 叶片的翼面轮廓具有限定腔室的内表面，并且通过两个相对的端部销连接到支撑结构，所述两个相对的端部销具有用于冷却空气通过并且在室内出来的相应开口; 该方法提供了形成具有多个孔并由彼此分离的第一和至少第二主体限定的插入件，并且每个尺寸接近但不大于至少一个开口的尺寸; 这些主体依次穿过销中的开口插入，并且位于室内，以将相对的空气流通过每个孔引导到翼面轮廓的内表面。

    TEST METHOD FOR TESTING A SOLID-PROPELLANT ROCKET ENGINE, SOLID-PROPELLANT ROCKET ENGINE AND SYSTEM FOR IMPLEMENTING THE METHOD
    10.
    发明申请
    TEST METHOD FOR TESTING A SOLID-PROPELLANT ROCKET ENGINE, SOLID-PROPELLANT ROCKET ENGINE AND SYSTEM FOR IMPLEMENTING THE METHOD 有权

    公开(公告)号：US20210190014A1

    公开(公告)日：2021-06-24

    申请号：US16755068

    申请日：2018-10-11

    Applicant: AVIO S.P.A.

    Inventor： Daniele SCHIARITI ,  Paolo BELLOMI

    IPC: F02K9/96 ,  F02K9/24 ,  F02K9/34 ,  F02K9/36

    Abstract: A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

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