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    Cooling System with a Bearing Compartment Bypass
    62.
    发明申请
    Cooling System with a Bearing Compartment Bypass 有权
    带有轴承舱的冷却系统旁路

    公开(公告)号：US20150285147A1

    公开(公告)日：2015-10-08

    申请号：US14594663

    申请日：2015-01-12

    Applicant: United Technologies Corporation

    Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/221 ,  F05D2260/232 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

    Abstract translation: 公开了一种用于向燃气涡轮发动机的涡轮部分提供缓冲冷却的冷却空气的冷却系统。 冷却系统可以包括构造成将冷却空气朝向涡轮机部分传送的第一管道，被配置为冷却从第一管道转向以提供缓冲空气的排出气流的热交换器，以及配置成引导至少一部分 的缓冲空气通过绕过燃气涡轮发动机的轴承室的至少一个通道。 冷却系统还可以包括歧管，其配置成允许从第一导管排出的冷却空气和离开旁路导管的缓冲空气混合并提供缓冲冷却的冷却空气;以及喷嘴组件，其配置成将缓冲冷却的冷却空气输送到 涡轮段。

    GAS TURBINE ENGINE BLADE WITH VARIABLE DENSITY AND WIDE CHORD TIP
    64.
    发明申请
    GAS TURBINE ENGINE BLADE WITH VARIABLE DENSITY AND WIDE CHORD TIP 审中-公开

    公开(公告)号：US20200024962A1

    公开(公告)日：2020-01-23

    申请号：US16397265

    申请日：2019-04-29

    Applicant: United Technologies Corporation

    Inventor： Pitchaiah Vijay Chakka ,  James D. Hill ,  David R. Pack

    IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28

    Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.

    Offset cores for gas turbine engines
    65.
    发明授权
    Offset cores for gas turbine engines 有权

    公开(公告)号：US10415466B2

    公开(公告)日：2019-09-17

    申请号：US14921575

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill

    IPC: F02C3/14 ,  F02C3/04 ,  F02K3/00 ,  F01D25/24 ,  F01D25/30 ,  F02K3/04 ,  F02C3/10

    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.

    AIRCRAFT THERMAL MANAGEMENT SYSTEM
    66.
    发明申请
    AIRCRAFT THERMAL MANAGEMENT SYSTEM 审中-公开

    公开(公告)号：US20190003391A1

    公开(公告)日：2019-01-03

    申请号：US16111870

    申请日：2018-08-24

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  James D. Hill ,  Gabriel L. Suciu ,  Brian Merry

    IPC: F02C7/14

    Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

    Offset core engine architecture
    70.
    发明授权
    Offset core engine architecture 有权

    公开(公告)号：US10024235B2

    公开(公告)日：2018-07-17

    申请号：US14608227

    申请日：2015-01-29

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill ,  Jesse M. Chandler

    IPC: F02C3/14 ,  F02C3/06 ,  F02C3/10 ,  F02C6/02 ,  F02C7/05 ,  F02K3/12

    Abstract: A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

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