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1.发明授权VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD 有权可变GEBLÄSEEINLASSLEITSCHAUFELANORDNUNG，这样的安排及相应的控制方法涡轮发动机
公开(公告)号：EP1831521B1
公开(公告)日：2008-08-20
申请号：EP04822146.9
申请日：2004-12-01
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
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公开(公告)号：EP1888905A1
公开(公告)日：2008-02-20
申请号：EP06748463.4
申请日：2006-03-16
CPC分类号： F01D11/005 , F02C3/073 , F02K3/06 , F02K3/068 , Y02T50/672
摘要： A fan-turbine rotor hub (64) includes an outer periphery scalloped by a multitude of elongated openings (114). Each elongated opening defines an inducer receipt section to receive an inducer section (66) and a hollow fan blade section (72). An inducer exit from each inducer section is located adjacent a core airflow passage (80) within each fan blade section to provide communication therebetween. A seal (131) is located between an inner fan blade mount (124) and a blade receipt section (122) to minimize airflow leakage between the inducer exit and the core airflow passage.
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3.发明授权Turbine blade cluster for a fan-turbine rotor assembly and method of mounting such a cluster 有权为这样的基团的组件的风扇转子的方法和涡轮机叶片簇
公开(公告)号：EP1834076B1
公开(公告)日：2011-04-06
申请号：EP04822123.8
申请日：2004-12-01
CPC分类号： F02C3/08 , F01D5/225 , F01D5/3007 , F02C3/073 , F02K3/068 , F05D2260/30 , F05D2260/33 , Y10T29/49245
摘要： A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.
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4.发明公开TIP TURBINE ENGINE COMPRISING TURBINE BLADE CLUSTERS AND RADIAL ATTACHMENT LOCK ARRANGEMENT THEREFOR 有权为这样的基团的组件的风扇转子的方法和涡轮机叶片簇
公开(公告)号：EP1834076A1
公开(公告)日：2007-09-19
申请号：EP04822123.8
申请日：2004-12-01
CPC分类号： F02C3/08 , F01D5/225 , F01D5/3007 , F02C3/073 , F02K3/068 , F05D2260/30 , F05D2260/33 , Y10T29/49245
摘要： A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.
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公开(公告)号：EP1831519B1
公开(公告)日：2010-08-04
申请号：EP04822081.8
申请日：2004-12-01
CPC分类号： F02C3/14 , F01D5/022 , F02C3/067 , F02C3/073 , F02K3/068 , F02K3/072 , F05D2260/40311 , Y02T50/673
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公开(公告)号：EP1888905B1
公开(公告)日：2010-05-12
申请号：EP06748463.4
申请日：2006-03-16
CPC分类号： F01D11/005 , F02C3/073 , F02K3/06 , F02K3/068 , Y02T50/672
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公开(公告)号：EP1834067B1
公开(公告)日：2008-11-26
申请号：EP04822135.2
申请日：2004-12-01
CPC分类号： F02C3/073 , F01D5/225 , F01D5/3007 , F02C3/08 , F02K3/068 , F05D2260/30 , Y10T29/49321
摘要： A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a diffuser includes axial installation and radial rotation. The clusters are axially installed, then rotated toward a radial stop in a direction which will maintain each cluster against the radial stop during operation of the fan-turbine rotor assembly. A multitude of turbine rotor ring stages may also be locked together to future increase the rigidity of the turbine
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8.发明公开
公开(公告)号：EP1825111A1
公开(公告)日：2007-08-29
申请号：EP04822094.1
申请日：2004-12-01
摘要： A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substratem (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54). For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).
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公开(公告)号：EP2798186A1
公开(公告)日：2014-11-05
申请号：EP12863020.9
申请日：2012-12-26
发明人： MERRY, Brian , SUCIU, Gabriel L. , NORRIS, James W. , SIRICA, Steven J. , SCHWARZ, Frederick M.
IPC分类号： F02K3/02
CPC分类号： F01D17/162 , F02C3/073 , F02C3/08 , F02C3/107 , F02C7/36 , F02C9/20 , F02K3/068 , F05D2270/02 , F05D2270/101 , F05D2270/301 , F05D2270/304 , Y02T50/671
摘要： A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section.
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公开(公告)号：EP2788603A1
公开(公告)日：2014-10-15
申请号：EP12787998.9
申请日：2012-10-31
CPC分类号： F02C7/36 , F02C3/145 , F02C7/32 , F02K3/105 , F05D2220/76 , F05D2260/4023 , F05D2260/96
摘要： A gas turbine engine has a variable overall pressure rate ("OPR."). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR.
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