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1. 发明授权

EP3346136B1 COMPRESSOR ROTOR BLADE SEALING ARRANGEMENT WITH A ROTATING SHROUD EXTENDING ALONG THE UPSTREAM HALF OF THE BLADE TIP ONLY 有权
公开(公告)号：EP3346136B1
公开(公告)日：2019-05-22
申请号：EP18156937.7
申请日：2007-03-28
申请人： IHI Corporation
发明人： GOTO, Shinya , MUROOKA, Takeshi
IPC分类号： F04D29/16 , F04D29/54 , F04D29/52 , F04D29/56

2. 发明授权

EP2811138B1 VANE COUPLING PART STRUCTURE AND JET ENGINE USING SAME 有权
标题翻译： VANE联轴器零件结构和喷气发动机使用相同
公开(公告)号：EP2811138B1
公开(公告)日：2018-05-09
申请号：EP13743758.8
申请日：2013-02-01
申请人： IHI Corporation
发明人： YAGI, Hiroyuki , ISHIGURE, Tadahiro , INADA, Takaomi , MUROOKA, Takeshi , MORITA, Hideo , HONDA, Tatsuhito
IPC分类号： F02C7/20 , F01D9/02 , F01D25/24 , F02C7/00 , F02K3/06 , F04D29/54 , F01D5/28
CPC分类号： F01D9/042 , F01D5/282 , F01D25/162 , F01D25/246 , F02C7/20 , F05D2260/31 , F05D2260/36 , Y02T50/672 , Y02T50/673
摘要： A coupling support member 33 including a pair of divided pieces 34, 34 is placed in a coupling part between a vane proximal end portion 21 of a guide vane 20 and an attachment flange 31f, and the pair of divided pieces 34, 34 are joined to the vane proximal end portion 21 from both the sides in the vane thickness direction. A linear protrusion 21b is formed on one of joint surfaces 21a, 21a of the vane proximal end portion 21 to the pair of divided pieces 34, 34. A groove 35b engaged with the linear protrusion 21b formed in the vane proximal end portion 21 is formed on one of respective joint surfaces 35a, 35a of the pair of divided pieces 34, 34 of the coupling support member 33. The vane proximal end portion 21 is held between the pair of divided pieces 34, 34 of the coupling support member 33, by the fastening force that is applied to the pair of divided pieces 34, 34 of the coupling support member 33 from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.

3. 发明授权

EP2594805B1 FAN ROTOR BLADE AND FAN 有权
公开(公告)号：EP2594805B1
公开(公告)日：2019-05-01
申请号：EP11806782.6
申请日：2011-07-12
申请人： IHI Corporation
发明人： MUROOKA, Takeshi , KUROKI, Hiroshi , KAJIWARA, Rintaro , OBUCHI, Kenro
IPC分类号： F04D29/38 , F01D5/28

4. 发明授权

EP2846047B1 ROTOR BLADE AND FAN 有权
公开(公告)号：EP2846047B1
公开(公告)日：2018-05-23
申请号：EP13785070.7
申请日：2013-04-23
申请人： IHI Corporation
发明人： MUROOKA, Takeshi
IPC分类号： B32B5/12 , F01D5/14 , F01D5/28 , F04D29/02 , F04D29/32 , F04D29/38
CPC分类号： F01D5/147 , B32B5/12 , B32B2260/023 , B32B2603/00 , F01D5/282 , F04D19/002 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2300/6034 , Y02T50/672
摘要： A rotor blade main body (37) includes multiple first composite sheet groups (51) and multiple second composite sheet groups (53) which are provided in a blade thickness direction (TD). Each first composite sheet group (51) includes multiple composite sheets (49) which are stacked one on another from a blade thickness center (TC) side toward a dorsal surface (39). Each second composite sheet group (53) includes multiple composite sheets (49) which are stacked one on another from the blade thickness center (TC) side toward a ventral surface (41). A composite direction (CD) of orientation directions of fibers in the multiple composite sheets (49) in each of the sheet groups (51, 53) inclines by 20 degrees to 45 degrees from a span direction (SD).

5. 发明公开

EP3249205A1 JET ENGINE 有权
标题翻译：喷气发动机
公开(公告)号：EP3249205A1
公开(公告)日：2017-11-29
申请号：EP15893346.5
申请日：2015-05-27
申请人： IHI Corporation
发明人： KIMURA, Takehiko , MUROOKA, Takeshi , KAMEI, Atsushi
IPC分类号： F02K3/06 , F02C7/00 , F02C7/042 , F02K1/16
CPC分类号： F02C9/20 , F01D17/162 , F02C3/04 , F02C7/042 , F02K1/16 , F02K1/165 , F02K3/06 , F05D2220/326 , F05D2220/327 , F05D2240/12 , F05D2270/02 , F05D2270/101 , Y02T50/671
摘要： A jet engine which includes: a fan (3, 31, 32, 33) provided with a plurality of stages of rotor blades (3b1, 3d1, 3g1, 3i1, 3k1); a compressor (4, 5) which compresses air which is sent from the fan (3, 31, 32, 33); a combustor (6) which generates combustion gas by using compressed air generated by the compressor (4, 5); a turbine (7, 8) which generates a driving force from the combustion gas; and a nozzle (11a) which discharges the combustion gas, the jet engine further includes: a variable guide vane (3f1, 3fa1, 3fb1, 3fc1) which is disposed upstream of the rotor blades (3d1, 3g1, 3i1, 3k1) of a second and later stage of the rotor blades (3b1, 3d1, 3g1, 3i1, 3k1) of the fan (3, 31, 32, 33) and which adjusts an inlet angle of air flow against the second and later stage of the rotor blades (3d1, 3g1, 3i1, 3k1); a fluid resistance adjusting device (11b) which adjusts a fluid resistance at the nozzle (11a); and a controller (12) which controls the variable guide vane (3f1, 3fa1, 3fb1, 3fc1) such that the inlet angle at the time of cruise flight is smaller than the inlet angle at the time of acceleration and controls the fluid resistance adjusting device (11b) such that increase in the fluid resistance, due to an increase in a volume flow at an outlet of the fan (3, 31, 32, 33) corresponding to a reduction in the inlet angle, is suppressed.
摘要翻译： 1。一种喷气发动机，其特征在于，具有：具有多级动叶片（3b1,3d1,3g1,3i1,3k1）的风扇（3,31,32,33）; 压缩机（4,5），压缩从风扇（3,31,32,33）送出的空气;压缩机燃烧器（6），其利用压缩机（4,5）产生的压缩空气产生燃烧气体; 从燃烧气体产生驱动力的涡轮机（7,8）和排出燃烧气体的喷嘴（11a），所述喷气发动机还包括：可变导向叶片（3f1,3fa1,3fb1,3fc1），所述可变导向叶片布置在所述转子叶片（3d1,3g1,3i1,3k1）风扇（3,31,32,33）的转子叶片（3b1,3d1,3g1,3i1,3k1）的第二级和后级，并且调节风扇相对于第二级和后级转子叶片的入口角度（3d1,3g1,3i1,3k1）; 调节喷嘴（11a）的流体阻力的流体阻力调节装置（11b）; 和控制器（12），其控制所述可变导向叶片（3f1,3fa1,3fb1,3fc1），使得巡航行驶时的入口角度小于加速时的入口角度，并且控制流体阻力调节装置（11b），使得由于风扇（3,31,32,33）的出口处的体积流量的增加而导致的流体阻力的增加被抑制，所述体积流量对应于入口角度的减小。

6. 发明公开

EP2096320A1 CASCADE OF AXIAL COMPRESSOR 有权
标题翻译：轴流压缩机级联
公开(公告)号：EP2096320A1
公开(公告)日：2009-09-02
申请号：EP07739809.7
申请日：2007-03-27
申请人： IHI Corporation
发明人： GOTO, Shinya , MUROOKA, Takeshi
IPC分类号： F04D29/54 , F04D29/38 , F04D29/66
CPC分类号： F04D29/324 , F04D21/00 , F04D29/544 , F04D29/661
摘要： In a blade row of an axial flow type compressor in which a rotor blade row and a stator blade row are alternately arranged in an axial direction, the stator blade row 10 is formed by plural main stator blades 12 and plural sub-stator blades 14. Each main stator blade 12 is formed by a basic blade portion 12a which has the same shape as that of each sub-stator blade and a forward blade portion 12b which extends to the upstream side of the basic blade portion. The basic blade portion 12a are located at the same position in an axial direction. The forward blade portion 12b forms a forward stator blade row which has a circumferential interval larger than that of the basic stator blade row in the vicinity of at least a radial inner end.
摘要翻译：在动叶片列和静叶片列在轴向上交替配置的轴流式压缩机的叶片列中，静叶片列10由多个主静叶片12和多个副静叶片14构成。每个主静叶片12由具有与每个副静叶片相同形状的基叶片部分12a和延伸到基叶片部分上游侧的前叶片部分12b形成。基本叶片部分12a位于轴向上的相同位置处。前叶片部分12b在至少径向内端附近形成前部静叶片列，该前部叶片列的周向间隔大于基本静叶片列的周向间隔。

7. 发明公开

EP3633207A1 BLADE FOR FAN AND COMPRESSOR 审中-公开
公开(公告)号：EP3633207A1
公开(公告)日：2020-04-08
申请号：EP17910748.7
申请日：2017-12-20
申请人： IHI Corporation
发明人： OKADA, Ryuichi , HAYASHI, Ryosuke , MUROOKA, Takeshi , ENOKI, Tomonori
IPC分类号： F04D29/38 , F02K3/04
摘要： To provide a blade of a fan or compressor that is reduced in loss by enlarging a laminar flow region over a blade surface. A blade according to the present disclosure is divided into a subsonic region where the relative Mach number of the inlet air flow during rated operation of a turbofan engine is lower than 0.8 and a transonic region where the relative Mach number is equal to or higher than 0.8. Provided that a parameter ( δ ) defined according to δ = ( β in- β )/( β in- β ex) is referred to as a blade surface angle change rate where β denotes an angle formed by a tangent to the blade surface and the axial direction of the turbofan engine, β in denotes the blade surface angle at the leading edge of the blade, and the β ex denotes the blade surface angle at the trailing edge, in each of the subsonic region and the transonic region, the minimum value of the blade surface angle change rate on the pressure surface, an upper limit value of the blade surface angle change rate at a predetermined axial location along the chord on the pressure surface, and an upper limit value and a lower limit value of the blade surface angle change rate at a predetermined axial location along the chord on the suction surface are defined.

8. 发明授权

EP2083175B1 STATOR BLADE AND ROTOR BLADE OF COMPRESSOR 有权
公开(公告)号：EP2083175B1
公开(公告)日：2018-07-25
申请号：EP07739979.8
申请日：2007-03-28
申请人： IHI Corporation
发明人： GOTO, Shinya , MUROOKA, Takeshi
IPC分类号： F04D29/16 , F04D29/54 , F04D29/52
CPC分类号： F04D29/164 , F01D5/143 , F01D5/225 , F01D11/001 , F01D11/08 , F04D29/321 , F04D29/526 , F04D29/563 , Y02T50/671 , Y02T50/673
摘要： A compressor stator blade 10 includes a seal mechanism 12 configured to hermetically seal a part between a radial inner end on the upstream side and an outer surface of a rotary body, and a remainder part on the downstream side of the seal mechanism includes a hub clearance 14 between the outer surface of the rotary body and itself. Additionally, a compressor rotor blade 20 includes a seal mechanism 22 configured to hermetically seal a part between a radial outer end on the upstream side and an inner surface of a stationary body, and a remainder part on the downstream side of the seal mechanism includes a tip clearance 24 between the inner surface of the stationary body and itself.

9. 发明公开

EP2660475A1 FAN ROTOR BLADE AND FAN 有权
标题翻译： LÜFTERROTORBLATTUNDLÜFTER
公开(公告)号：EP2660475A1
公开(公告)日：2013-11-06
申请号：EP11854281.0
申请日：2011-12-16
申请人： IHI Corporation
发明人： MUROOKA, Takeshi
IPC分类号： F04D29/38
摘要： A fan rotor blade has a rotor blade leading edge 41. On a hub side of the rotor blade leading edge 41, a vertical hub section 49 is formed. From a top end of the vertical hub section 49 to a mid-span side of the rotor blade leading edge 41, a backward tilt mid-span section 51 is formed. From a top end of the backward tilt mid-span section 51 to a tip end of the rotor blade leading edge 41, a forward tilt tip section 53 is formed. From a hub end of the rotor blade leading edge 41 to a base end of the vertical hub section 49, a backward tilt hub section 55 is formed. The backward tilt hub section 55 is backwardly tilted so that a top end thereof is positioned behind a base end thereof.
摘要翻译：风扇转子叶片具有转子叶片前缘41.在转子叶片前缘41的毂侧，形成有垂直毂部49。从垂直轮毂部分49的顶端到转子叶片前缘41的中跨侧，形成一个向后倾斜的中跨段51。从向后倾斜中跨部51的顶端到转子叶片前缘41的前端，形成有前倾侧端部53。从转子叶片前缘41的轮毂端到垂直轮毂部49的基端，形成向后倾斜轮毂部55。向后倾斜的毂部55向后倾斜，使得其顶端位于其基端的后方。

10. 发明公开

EP2037126A1 TUBOFAN ENGINE 审中-公开
标题翻译： TUBOFAN发动机
公开(公告)号：EP2037126A1
公开(公告)日：2009-03-18
申请号：EP07741180.9
申请日：2007-04-06
申请人： IHI Corporation
发明人： KODAMA, Hidekazu , GOTO, Shinya , MIZUTA, Ikuhisa , MUROOKA, Takeshi
IPC分类号： F04D29/38 , F02K3/06
CPC分类号： F04D29/384 , F01D5/141 , Y02T50/671 , Y02T50/673
摘要： A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.
摘要翻译：用于将空气吸入其中的风扇第一级旋转叶片10的轮毂侧前缘部分比前端侧前缘部分和中间跨度前缘部分更向发动机的前方延伸。风扇第一级旋转叶片10的轮毂侧与前端侧和中间跨度一体连接，同时具有比翼尖侧和中间跨度更长的弦长。轮毂侧前缘部的根部的半径设定为0〜0.4的轮毂比。

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