-
公开(公告)号：EP1828567B1
公开(公告)日：2011-10-12
申请号：EP04822103.0
申请日：2004-12-01
摘要： A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.
-
2.发明公开
公开(公告)号：EP1834067A1
公开(公告)日：2007-09-19
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
-
公开(公告)号：EP1828545A2
公开(公告)日：2007-09-05
申请号：EP04822062.8
申请日：2004-12-01
IPC分类号： F01D5/30
摘要： A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.
-
4.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.
-
5.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.
-
公开(公告)号：EP1834071A1
公开(公告)日：2007-09-19
申请号：EP04822082.6
申请日：2004-12-01
CPC分类号： F01D5/022 , F02C3/073 , F02C3/08 , F02K3/068 , F05D2260/60 , Y02T50/672
摘要： A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted toward a rotational direction of the fan-turbine rotor assembly such that the inducer inlet section operates as an air scoop during rotation of the fan-turbine rotor assembly. Both axial and centrifugal compression of the airflow occurs within the inducer passage section to effectively pump the airflow through the inducer section and into the core airflow passage.
-
公开(公告)号：EP1828683B1
公开(公告)日：2013-04-10
申请号：EP04822059.4
申请日：2004-12-01
-
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.
-
公开(公告)号：EP1841959A1
公开(公告)日：2007-10-10
申请号：EP04822061.0
申请日：2004-12-01
CPC分类号： F02C3/073 , F01D5/18 , F02K3/068 , F04D25/045 , F04D29/321 , Y02T50/673 , Y02T50/676
摘要： A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section (66), a hollow fan blade section (72) and a diffuser section (74). The hollow fan blade section defines a airflow passage (80). The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes (122). The airflow streams are then further turned by discharge turning vanes (124) before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.
-
公开(公告)号：EP1828683A1
公开(公告)日：2007-09-05
申请号：EP04822059.4
申请日：2004-12-01
IPC分类号： F23R3/28
摘要： A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to an outlet that provides fuel to an interior chamber of the combustor. In one embodiment, front portions of the inner and outer walls curve toward one another and overlap to form an annular gap or manifold through which fuel is distributed to the combustion chamber.
-
-
-
-
-
-
-
-
-
搜索结果
20 条记录 (耗时 0.013 秒)
