公开(公告)号：US20190323359A1

公开(公告)日：2019-10-24

申请号：US16378800

申请日：2019-04-09

Applicant: ROLLS-ROYCE plc

Inventor： Peter T. IRELAND ,  Nicholas Russell GREEN ,  Eduardo ROMERO ,  Gladys C. NGETICH

IPC: F01D5/18 ,  F01D25/12 ,  B23P15/02

Abstract: Disclosed herein is a method of manufacturing a double walled section of an aerofoil (701) of a gas turbine engine (10), the method comprising: forming a plurality of columns (402) on an outer surface of a first structure; forming a plurality of columns (402) on a surface of each of a plurality of parts of a second structure; and forming a double walled section of an aerofoil (701) by attaching the ends of columns (402) on each part of the second structure to the ends of columns (402) on the first structure such that the first structure is an inner wall (401) of the section of the aerofoil (701) and the second structure is an outer wall (501) of the section of the aerofoil (701).

公开(公告)号：US20200224875A1

公开(公告)日：2020-07-16

申请号：US16720412

申请日：2019-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Alexander V. MURRAY ,  Peter T. IRELAND ,  Eduardo ROMERO ,  Anthony J. RAWLINSON

IPC: F23R3/00

Abstract: There is disclosed wall cooling system 50 having a double-wall geometry. A first wall 55 and a second wall 60 extend over a plan area with the second wall spaced from the first wall by a gap. The first wall 55 has multiple upstanding members 65 spanning the gap and contacting the second wall 60 such that the first and second walls are mechanically and thermally connected. The first wall 55 is shaped so as to provide a two-dimensional array of crests 85 and recesses 90. The crests 85 are spaced from the second wall 60. The first wall 55 has a plurality of through-holes 70 for flow of coolant through the first wall and into the gap. The cooling system 50 is suitable for use in a gas turbine engine 10, for example in the turbine 17, 19.

公开(公告)号：US20230296025A1

公开(公告)日：2023-09-21

申请号：US18067961

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter T. IRELAND ,  John COULL ,  João António Coelho VIEIRA

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202

Abstract: A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.

公开(公告)号：US20160169003A1

公开(公告)日：2016-06-16

申请号：US14944947

申请日：2015-11-18

Applicant: ROLLS-ROYCE PLC

Inventor： Tsun H. WONG ,  Peter T. IRELAND ,  Kevin P. SELF

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/30 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component, e.g. an aerofoil component like a turbine-blade or guide-vane, for a gas turbine engine, including first and second walls defining at least one passage for supply of cooling fluid to a portion of the component to be cooled, the portion including a slot via which cooling fluid passes from the passage to exit of slot for effecting cooling of the portion, wherein the slot includes at least one side wall, pair of opposite side walls, each having surface profile defining array of channels for passage of cooling fluid, and surface profile defining each of arrays of channels is undulating with the respective arrays of channels in two side walls being angled with respect to one another. The resulting internal cross-corrugated cooling arrangement promotes enhanced cooling of the trailing edge or other portion of the component by controlling flow rate of cooling air through slot and exhausted therefrom.

Abstract translation: 组分，例如 包括用于燃气涡轮发动机的诸如涡轮机叶片或导向叶片的机翼部件，包括限定用于将冷却流体供应到待冷却部件的一部分的至少一个通道的第一和第二壁，所述部分包括槽通孔 所述冷却流体从所述通道流出到所述槽的出口以实现所述部分的冷却，其中所述狭槽包括至少一个侧壁，一对相对的侧壁，每个侧壁具有限定用于冷却流体通过的通道阵列的表面轮廓，以及表面 限定每个通道阵列的轮廓波动，两个侧壁中的相应的通道阵列相对于彼此成角度。 所产生的内部交叉波纹状冷却装置通过控制冷却空气通过狭槽并从其排出的流量来促进后缘或部件的其它部分的增强的冷却。

公开(公告)号：US20160010558A1

公开(公告)日：2016-01-14

申请号：US14748787

申请日：2015-06-24

Applicant: ROLLS-ROYCE PLC

Inventor： Zahid M. HUSSAIN ,  Nityabh MISHRA ,  Peter T. IRELAND

IPC: F02C7/25 ,  F02K3/075 ,  F02C9/18

CPC classification number: F02C7/25 ,  F01D17/105 ,  F02C7/042 ,  F02C9/18 ,  F02K3/075

Abstract: A ventilation inlet including a conduit (104) arranged to convey flow from a first flow zone to a second flow zone. The conduit has a mouth region (106) presenting to the first flow zone an entrance aperture to receive the flow therefrom. The conduit has a baffle (114) spanning a portion of the conduit to define a throat region (116), the throat region being narrower than the entrance aperture. The throat region (116) is movable along the conduit (104) to control the flow through the ventilation inlet.

Abstract translation: 通风入口，其包括布置成将流从第一流动区域输送到第二流动区域的导管（104）。 导管具有向第一流动区域呈现入口孔口的口部区域（106），用于接收来自其的流体。 导管具有跨过管道的一部分以限定喉部区域（116）的挡板（114），所述喉部区域比入口孔窄。 喉部区域116可沿导管104移动以控制通过通气入口的流动。