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公开(公告)号：EP3301261A1
公开(公告)日：2018-04-04
申请号：EP17187066.0
申请日：2017-08-21
申请人： Rolls-Royce plc
发明人： Mottram, Martin , Sellers, Paul
CPC分类号： F01D5/187 , F01D5/147 , F01D5/20 , F05D2220/32 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202
摘要： A blade comprises a root portion and an elongate portion extending from the root portion to a tip. The elongate portion has an aerofoil-shaped cross section having a leading edge, a trailing edge (42), a suction side (44) and a pressure side. The tip may optionally include a squealer defining a gutter (46) at the tip. The squealer comprises a wall (45) extending from the trailing edge (42) and along a substantial portion of the perimeter of the tip. A main trailing edge cooling channel (47) extends within the elongate portion in a direction from root to tip adjacent the trailing edge (42) and exiting into the gutter (46). A gallery channel (48) is arranged just behind the gutter (46) and extends from an open end (28a) intersecting the main trailing edge cooling channel (47) to a closed end (28b) located just behind an apogee of the trailing edge (42). A plurality of film cooling channels extends from the gallery channel (48) and through the squealer wall (45) and the gallery channel (48) has a greater diameter at the open end than at the closed end. The arrangement is also applicable to winglet tip and flat tip shroudless blades.
摘要翻译： 叶片包括根部和从根部延伸至尖端的细长部分。 细长部分具有翼型横截面，该翼型横截面具有前缘，后缘（42），吸力侧（44）和压力侧。 尖端可以可选地包括在尖端限定沟槽（46）的凹槽。 凹槽器包括从后缘（42）延伸并沿着尖端的周边的大部分延伸的壁（45）。 主后缘冷却通道（47）在细长部分内沿着从后缘（42）的根部到顶端的方向延伸并且退出到沟槽（46）中。 甲画廊信道（48）的后方装备有檐槽（46）和从开口端（28a）的相交的主后缘冷却通道（47）到位于后面的后缘的最高点的闭合端（28B）延伸 （42）。 多个膜冷却通道从通道通道（48）延伸并穿过回声壁（45），并且通道通道（48）在开口端比在封闭端具有更大的直径。 这种安排也适用于小翼尖端和扁平尖端无护罩叶片。
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公开(公告)号：EP3301262A1
公开(公告)日：2018-04-04
申请号：EP17187258.3
申请日：2017-08-22
申请人： Rolls-Royce plc
IPC分类号： F01D5/20
CPC分类号： F01D5/186 , F01D5/141 , F01D5/20 , F05D2240/304 , F05D2240/307 , F05D2250/314 , F05D2250/52 , F05D2260/202
摘要： A blade comprises a root portion and an elongate portion extending from the root portion to a tip, the elongate portion having an aerofoil-shaped cross section. The aerofoil has a leading edge (53), a trailing edge (54), a suction side (51) and a pressure side (52). The tip includes a squealer defining a gutter (57) at the tip wherein the squealer comprises a wall (56) extending from the trailing edge (54) along the entirety of a first of the suction side (51) and pressure side (52), around the leading edge (53) and partly along a second of the suction side (51) and pressure side (52) leaving a gap between the trailing edge (54) and an end of the wall (56b) on the second side. A main trailing edge cooling channel (58a) extends within the elongate portion in a direction from root to tip adjacent the trailing edge (54) and exits into the gutter (57). The main trailing edge cooling channel (58a) includes a bend just downstream of the exit such that the exit is displaced from a camber line (C-C) of the blade elongated portion towards the second side.
摘要翻译： 叶片包括根部和从根部延伸至尖端的细长部分，细长部分具有翼型横截面。 机翼具有前缘（53），后缘（54），吸力侧（51）和压力侧（52）。 尖端包括在尖端限定沟槽（57）的凹槽，其中凹槽包括沿着抽吸侧（51）和压力侧（52）中的第一个的整体从后缘（54）延伸的壁（56） ，围绕前缘（53）并且部分地沿吸力侧（51）和压力侧（52）的第二部分留下后缘（54）和第二侧上的壁（56b）的端部之间的间隙。 主后缘冷却通道（58a）在细长部分内在从后缘（54）附近的根部到前端的方向上延伸并且排出到沟槽（57）中。 主后缘冷却通道（58a）包括恰好在出口下游的弯曲部，使得出口从叶片细长部分的弧线（C-C）向第二侧移位。
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公开(公告)号：EP3670834A1
公开(公告)日：2020-06-24
申请号：EP19210229.1
申请日：2019-11-20
申请人： Rolls-Royce plc
发明人： Mottram, Martin
摘要： A turbine blade having a body enclosing a plurality of internal channels for the passage of coolant gas received through an inlet (32) formed in the blade root, comprising a gas flow separator (30), configured to separate coolant gas into first (35) and second (36) gas flows. The gas flow separator is configured to separate the first and second gas flows such that the level of contaminants in the first gas flow is lower than the level of contaminants in the second gas flow.
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公开(公告)号：EP3561231A1
公开(公告)日：2019-10-30
申请号：EP19165064.7
申请日：2019-03-26
申请人： Rolls-Royce plc
发明人： Mottram, Martin
IPC分类号： F01D5/18
摘要： A component 50 for a gas turbine engine, comprising:
a first wall 62 defining an exterior surface of the component;
a second wall 61, arranged such that a coolant channel 63 is defined by the space between the first and second walls; and
a plurality of apertures 71,72;83,84;95,96 provided through the first wall to connect the coolant channel to the exterior surface of the component;
wherein adjacent at least one aperture 72;84;95 the coolant channel comprises a flow modifier 70;80;90, configured to locally change the pressure of the coolant flowing in the coolant channel in the region of the aperture relative to a region of the coolant channel adjacent another aperture 71;83;96.-
公开(公告)号：EP3533532A1
公开(公告)日：2019-09-04
申请号：EP19155458.3
申请日：2019-02-05
申请人： Rolls-Royce plc
发明人： Mottram, Martin
摘要： A core (400) for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core (400), the core (400) comprising: a first core passage (401) having a first point (405) and a second point (406) therein and including no straight path between the first point (405) and the second point (406); and a first core bridge (421a) which extends away from the first core passage (401) between the first and second points (405, 406), wherein the first core bridge (421a) comprises a first pillar (422) and a second pillar (412a) which connect to the first and second points (405, 406) respectively, and a bridge portion (423a) which extends between the first and second pillars (422, 412a); wherein the first pillar (422) comprises a core inlet portion (408) having a thickness at the first point (405) and the second pillar (412a) has a thickness at the second point (406), the thickness of the core inlet portion (408) at the first point (405) being less than the thickness of the second pillar (412a) at the second point (406).
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公开(公告)号：EP3301261B1
公开(公告)日：2019-07-17
申请号：EP17187066.0
申请日：2017-08-21
申请人： Rolls-Royce plc
发明人： Mottram, Martin , Sellers, Paul
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公开(公告)号：EP3179039A1
公开(公告)日：2017-06-14
申请号：EP16198589.0
申请日：2016-11-14
申请人： Rolls-Royce plc
发明人： Mottram, Martin
CPC分类号： F01D5/187 , F01D5/186 , F01D9/02 , F01D9/065 , F01D11/08 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/11 , F05D2240/122 , F05D2240/304 , F05D2240/81 , F05D2250/314 , F05D2260/202 , F23R3/002
摘要： An aerofoil (36) for a gas turbine engine (10) comprising a pressure wall (48) and a suction wall (49) and defining leading and trailing edges (43, 45), the walls define a passage (61) into which is supplied a cooling fluid, an array of cooling holes (60) is provided through at least one of the walls (48, 49) to allow the cooling fluid to flow from an interior surface (55) to an exterior surface (56). The array of holes (60) comprise two groups (62, 64), the holes of each group are angled to intersect the holes of the other group and are characterised in that the holes of at least one of the groups (62, 64) comprises two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.
摘要翻译： 一种用于燃气涡轮发动机（10）的机翼（36），其包括压力壁（48）和吸力壁（49）并且限定前缘和后缘（43,45），所述壁限定通道（61） 提供冷却流体，通过壁（48,49）中的至少一个提供冷却孔阵列（60），以允许冷却流体从内表面（55）流到外表面（56）。 孔阵列（60）包括两个组（62,64），每个组的孔都成角度以与另一个组的孔相交并且其特征在于至少一个组（62,64） 包括彼此成不同角度的两个或更多个孔以改变壁的孔隙率以考虑另外改变的壁温度。 对于给定的冷却剂质量流量，这种布置还允许较少的冷却剂质量流量保持恒定的金属温度或较低的金属温度。
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