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33 records (took 0.088 seconds)

    22.
    发明专利
    未知

    公开(公告)号：DE602004019709D1

    公开(公告)日：2009-04-09

    申请号：DE602004019709

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    IPC: F02C3/073 ,  F02K3/068 ,  F23R3/52

    Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

    23.
    发明专利
    未知

    公开(公告)号：DE602004018045D1

    公开(公告)日：2009-01-08

    申请号：DE602004018045

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A

    IPC: F01D5/22 ,  F01D5/30 ,  F02C3/073 ,  F02C3/08 ,  F02K3/068

    Abstract: 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.

    24.
    发明专利
    未知

    公开(公告)号：DE60305425T2

    公开(公告)日：2006-10-12

    申请号：DE60305425

    申请日：2003-12-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NORRIS JAMES W ,  TWELVES WENDELL V

    IPC: F02K7/06 ,  F02C3/16 ,  F02C5/02 ,  F02C5/04 ,  F02C5/11 ,  F02C5/12 ,  F02K3/06 ,  F02K3/075 ,  F02K7/02 ,  F02K7/075 ,  F02K7/20

    Abstract: A pulsed combustion device includes a support structure (25) and a combustor carousel (52) supported by the support structure (25) and rotating relative thereto about an axis (500). The carousel (52) has a number of combustion conduits (50) in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge. A venturi effect may help control fuel/air charge leakage from a flowpath spanning the carousel (52) and a stationary manifold (60).

    29.
    发明专利
    未知

    公开(公告)号：AT470050T

    公开(公告)日：2010-06-15

    申请号：AT05252294

    申请日：2005-04-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GRABIEL L ,  NORRIS JAMES W

    IPC: F01D5/06 ,  F01D11/00 ,  G11B33/14

    Abstract: A gas turbine engine rotor stack (32) includes one or more longitudinally outwardly concave spacers (62C). The spacers may provide a longitudinal compression force that increases with rotational speed.

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