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    COMBUSTION CHAMBER
    11.
    发明申请
    COMBUSTION CHAMBER 审中-公开

    公开(公告)号：US20170307221A1

    公开(公告)日：2017-10-26

    申请号：US15467603

    申请日：2017-03-23

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul A. HUCKER ,  Steven BALLANTYNE ,  Stephen C. HARDING

    IPC: F23R3/46 ,  F23R3/60

    Abstract: A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. A frame structure at the downstream end of each segment has multiple spaced radially extending holes. The downstream end of each segment has an axially upstream extending groove and the downstream ring structure has an annular axially upstream extending hook which locates in the groove of each segment. A portion of the downstream ring structure abuts the frame structure of each segment. The downstream ring structure has multiple holes through the portion abutting the frame structure and segment is removably secured to the downstream ring structure by multiple fasteners locating in the holes in the segments and the downstream ring structure.

    FUEL INJECTOR
    12.
    发明申请
    FUEL INJECTOR 审中-公开
    喷油器

    公开(公告)号：US20170009991A1

    公开(公告)日：2017-01-12

    申请号：US15179495

    申请日：2016-06-10

    Applicant: ROLLS-ROYCE plc

    Inventor： Jonathan F. CARROTTE ,  Stephen C. HARDING ,  Ashley G. BARKER

    IPC: F23R3/20 ,  F23R3/34 ,  F02C7/22

    CPC classification number: F23R3/20 ,  F02C7/222 ,  F23D11/107 ,  F23D2206/10 ,  F23D2900/11401 ,  F23R3/343 ,  F23R2900/00014

    Abstract: A fuel injection system for a gas turbine engine (10) comprises; a pilot fuel injector section (22, 23) and a main airblast fuel injector section (25, 26, 27, 28, 29), the main airblast fuel injector section having an aft end (29) facing a combustion chamber (30). A surface of the injection system exposed to air flow through an injection system is non-axisymmetric or non-planar in a reference circumferential plane and/or is configured to generate controlled and varying acoustic impedance at or adjacent the aft end where, in use, the air flow collides with an oncoming acoustic wave.

    Abstract translation: 一种用于燃气涡轮发动机（10）的燃料喷射系统，包括： 主燃料喷射器部分（22,23）和主喷气燃料喷射器部分（25,26,27,28,29），主喷油器燃料喷射器部分具有面向燃烧室（30）的后端（29）。 暴露于通过注射系统的空气流动的注射系统的表面在参考圆周平面中是非轴对称的或非平面的，和/或被构造成在后端或邻近尾端处产生受控和变化的声阻抗， 空气流与迎面而来的声波相撞。

    COMBUSTOR APPARATUS
    13.
    发明申请
    COMBUSTOR APPARATUS 有权

    公开(公告)号：US20240392969A1

    公开(公告)日：2024-11-28

    申请号：US18652143

    申请日：2024-05-01

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen C. HARDING

    IPC: F23R3/28 ,  F02C3/06 ,  F23D11/10

    Abstract: A combustor assembly for a gas turbine engine comprises a combustor casing, and an integer quantity N of fuel swirl nozzles. The combustor casing defines a total internal volume of the combustor casing V (cm3) together with a Fuel Swirl Nozzle Density ratio (m−3) that is defined as: D F ⁢ S ⁢ N = N V and the DFSN parameter is a value in the range of 200 to 1,500.

    A METHOD OF MANUFACTURING A COMPONENT
    14.
    发明公开
    A METHOD OF MANUFACTURING A COMPONENT 审中-公开

    公开(公告)号：US20240051027A1

    公开(公告)日：2024-02-15

    申请号：US18359352

    申请日：2023-07-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen C. HARDING

    IPC: B22F10/47 ,  B22F10/85 ,  B33Y10/00 ,  B33Y50/02

    CPC classification number: B22F10/47 ,  B22F10/85 ,  B33Y10/00 ,  B33Y50/02 ,  B22F10/28

    Abstract: Disclosed is a method of manufacturing a component, the method comprising: determining a predicted direction and extent of distortion of a portion of the component; designing a support structure based on the predicted direction and extent of distortion of the portion of the component; additive manufacturing, by melting and fusing powder from a build plate, the component and the support structure. The support structure comprises, a hook structure comprising an elongate arm and a hook protruding from the elongate arm. The hook is deposited to abut a distortion surface of the component to restrain distortion of the component. The distortion surface is the furthest in the direction of distortion of the component. The elongate arm is deposited to extend from the hook in a direction having a vector component opposing the direction of distortion such that shrinkage of the elongate arm provides a force to minimise distortion of the component.

    COMBUSTION CHAMBER AND A COMBUSTION CHAMBER SEGMENT
    16.
    发明申请
    COMBUSTION CHAMBER AND A COMBUSTION CHAMBER SEGMENT 审中-公开
    燃烧室和燃烧室分段

    公开(公告)号：US20170045227A1

    公开(公告)日：2017-02-16

    申请号：US15217142

    申请日：2016-07-22

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen C. HARDING ,  Paul A. HUCKER ,  Giuseppe RALLO

    IPC: F23R3/00 ,  F02C3/04

    CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03041 ,  F23R2900/03044

    Abstract: A combustion chamber includes at least one annular wall which includes at least one box like structure and each box like structure includes an inner wall, outer wall, upstream end wall and downstream end wall. The inner wall is spaced radially from the outer wall and the outer wall has a plurality of apertures for the supply of coolant into the box like structure. The inner wall, the outer wall, the upstream end wall and the downstream end wall are integral. The upstream end of the annular wall has features to secure the annular wall to an upstream ring structure and a downstream end of the annular wall has features to mount the annular wall on a downstream ring structure. The inner wall has at least one slot extending through the full thickness of the inner wall to accommodate differential thermal expansion between the inner wall and the outer wall.

    Abstract translation: 燃烧室包括至少一个包括至少一个盒状结构的环形壁，并且每个盒状结构包括内壁，外壁，上游端壁和下游端壁。 内壁与外壁径向间隔开，并且外壁具有多个用于将冷却剂供应到盒状结构中的孔。 内壁，外壁，上游端壁和下游端壁是一体的。 环形壁的上游端具有将环形壁固定到上游环结构的特征，并且环形壁的下游端具有将环形壁安装在下游环结构上的特征。 内壁具有延伸穿过内壁的整个厚度的至少一个槽，以适应内壁和外壁之间的不同的热膨胀。

    METHOD AND APPARATUS FOR TESTING OF ENGINE COMPONENTS
    17.
    发明申请
    METHOD AND APPARATUS FOR TESTING OF ENGINE COMPONENTS 有权
    用于测试发动机部件的方法和装置

    公开(公告)号：US20160195474A1

    公开(公告)日：2016-07-07

    申请号：US14978498

    申请日：2015-12-22

    Applicant: ROLLS-ROYCE plc

    Inventor： Nicholas A. WORTH ,  Stephen C. HARDING

    IPC: G01N21/53 ,  G01N21/64 ,  G01M15/14

    CPC classification number: G01N21/53 ,  B23P2700/06 ,  F01D5/186 ,  F01D21/003 ,  F05D2260/202 ,  F05D2260/607 ,  F05D2260/83 ,  G01M15/14 ,  G01N21/64 ,  G01N21/95692 ,  G01N2201/023

    Abstract: Method and apparatus testing engine component, for blockage of one or more through-holes in a portion of a wall. The method including (i) providing a supply of test fluid, (ii) causing or permitting flow of test fluid to occur from first to second region, (iii) illuminating the second region with electromagnetic radiation to cause scattering of electromagnetic radiation by material exiting substantially non-blocked through-holes in wall portion having passed therethrough from the first to second side, (iv) detecting said scattering of electromagnetic radiation from said substantially non-blocked through-holes; and (v) comparing said detected scattering of electromagnetic radiation from said substantially non-blocked holes with known pattern of through-holes in component wall portion to determine the presence and/or location and/or identity of any blocked or partially blocked through-holes in component wall portion.

    Abstract translation: 方法和装置测试发动机部件，用于堵塞壁的一部分中的一个或多个通孔。 该方法包括（i）提供测试流体的供应，（ii）引起或允许测试流体从第一到第二区域发生的流动，（iii）用电磁辐射照射第二区域，以通过材料离开而使电磁辐射散射 从第一至第二侧通过的壁部分中的基本上未堵塞的通孔，（iv）检测来自所述基本上未堵塞的通孔的电磁辐射的散射; 和（v）将来自所述基本上未堵塞的孔的所述检测到的电磁辐射的散射与组件壁部分中的已知图案的通孔进行比较，以确定任何阻塞或部分阻挡的通孔的存在和/或位置和/或身份 在组件壁部分中。

    COMBUSTOR ARRANGEMENT
    19.
    发明申请
    COMBUSTOR ARRANGEMENT 有权

    公开(公告)号：US20220082055A1

    公开(公告)日：2022-03-17

    申请号：US17403081

    申请日：2021-08-16

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Giuseppe RALLO ,  Iain MORGAN

    IPC: F02C7/36 ,  F23R3/00

    Abstract: A combustion chamber comprising a plurality of circumferentially arranged cassette segments coupled to a combustor head at one end and a wall section at the other end, each cassette segment extending the full length of the combustion chamber, and wherein the combustor head has an annular tongue structure on a mating surface, the tongue structure engages with a groove portion present in each of the cassettes so that when assembled the groove portions in the each of the plurality of cassette segments forms a substantially continuous groove.

    FUEL INJECTOR
    20.
    发明申请
    FUEL INJECTOR 审中-公开

    公开(公告)号：US20180195726A1

    公开(公告)日：2018-07-12

    申请号：US15862724

    申请日：2018-01-05

    Applicant: ROLLS-ROYCE plc

    Inventor： Frederic WITHAM ,  Steven BALLANTYNE ,  Jonathan M. GREGORY ,  Mike OJ CARUSO ,  Stephen C. HARDING

    IPC: F23R3/28 ,  F23R3/38 ,  F23R3/34 ,  F23R3/20 ,  F23R3/14 ,  F02C7/22 ,  F23D11/38 ,  F23D11/10 ,  F02C9/28

    Abstract: A fuel injector comprises an elongate fuel passage (31) having an elongate axis (31a) extending from an upstream inlet end to a downstream outlet end. A plurality of outlets (33) is arranged at the outlet end, each outlet extends obliquely with respect to the elongate axis (31a). The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defines a first annular cavity (34) between the inner skin and an outer skin. The inner skin and the outer skin meet adjacently upstream of the one or more outlets to close an end of the first annular cavity (34). The injector has a nose section (32) at a downstream end, the nose section (32) being convergent and fluted. The flutes (38) are arranged between the outlets (33) and extend towards the downstream end of the nose section (32) whereby to guide an air stream (A) passing over the injector (30) to form single jet at the downstream end of the nose section (32).

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