公开(公告)号：US20170314562A1

公开(公告)日：2017-11-02

申请号：US15143412

申请日：2016-04-29

Applicant: United Technologies Corporation

Inventor： Becky E. Rose

IPC: F04D25/02 ,  F02K3/06 ,  F04D29/32

CPC classification number: F04D25/024 ,  F01D5/141 ,  F01D5/147 ,  F01D9/041 ,  F02K3/06 ,  F04D29/321 ,  F05B2220/303 ,  F05B2230/00 ,  F05D2240/12 ,  F05D2240/301 ,  F05D2260/4031 ,  Y02T50/672 ,  Y02T50/673

Abstract: A propulsor for a gas turbine engine includes, among other things, a case including a duct disposed along an axis to define a flow path. A rotor includes a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path. A row of guide vanes are situated in the flow path. At least two of the guide vanes extend in the generally radial direction between inner and outer surfaces of the duct, extends in a chordwise direction between a first leading edge and a first trailing edge to define a vane chord dimension (VCD) at a first span position of the corresponding guide vane, and defines a vane circumferential pitch (VCP) at the first span position of the corresponding guide vane and an adjacent one of the guide vanes. The row of guide vanes has a vane solidity (VR) defined as VCD/VCP, the vane solidity (VR) being equal to or less than 1.43.

公开(公告)号：US09771856B2

公开(公告)日：2017-09-26

申请号：US14797446

申请日：2015-07-13

Applicant: TOYOTA JIDOSHA KABUSHIKI KAISHA

Inventor： Hidefumi Nakao

IPC: F02B33/40 ,  F04D17/10 ,  F04D25/02 ,  F04D27/02 ,  F04D29/28 ,  F04D29/42 ,  F04D29/68 ,  F04D29/44

CPC classification number: F02B33/40 ,  F04D17/10 ,  F04D25/02 ,  F04D27/0207 ,  F04D29/284 ,  F04D29/4206 ,  F04D29/4213 ,  F04D29/444 ,  F04D29/685 ,  F05D2250/51

Abstract: A centrifugal compressor having a casing that houses an impeller allowing rotation about a rotational axis C, a gas channel, a treatment hollow part provided inside the casing, a first channel open to the gas channel on the downstream side of the blade leading edge of the impeller, a second channel open to the gas channel at the upstream side of the blade leading edge, a guide vane that imparts a swirl component in an opposite rotational direction of the impeller to gas discharged from the second channel, a constricting part that constricts the gas channel, and a rectifying part that rectifies gas in a direction that minimizes the swirl component about the rotational axis C and also increases the component in the direction of the rotational axis C.

公开(公告)号：US20170268534A1

公开(公告)日：2017-09-21

申请号：US15458725

申请日：2017-03-14

Applicant: TRANE INTERNATIONAL INC.

Inventor： Ryan SULLIVAN ,  Joseph R. ORR ,  Brian F. LONG ,  Daniel T. NIBLICK

IPC: F04D29/60 ,  F04D29/053 ,  F16M1/04 ,  F04D25/02

CPC classification number: F04D29/601 ,  F04D17/16 ,  F04D25/02 ,  F04D25/06 ,  F04D25/08 ,  F04D29/053 ,  F04D29/626 ,  F16M1/04

Abstract: Aligning a motor shaft in a fan assembly is described. Aligning a centerline of a motor shaft in a direct drive fan assembly includes selecting a motor from among a plurality of motors and matching a motor-plate from among a plurality of motor plates to the motor, the matched motor plate is based on the selected motor.Aligning the centerline further includes creating, from the selected motor and the matching motor plate, a motor-plate assembly that has a resulting height, where the resulting height of the motor-plate assembly corresponds to a particular height of a direct drive fan assembly, and aligning the centerline of a motor shaft of the motor-plate assembly to the direct drive fan assembly, where the particular height of the direct drive fan assembly is constant.

公开(公告)号：US20170254335A1

公开(公告)日：2017-09-07

申请号：US15059950

申请日：2016-03-03

Applicant: HAMILTON SUNDSTRAND CORPORATION

Inventor： Eric O. Varland

IPC: F04D25/02 ,  F04D29/32 ,  F04D29/52 ,  F04D25/08

CPC classification number: F04D25/026 ,  F04D19/002 ,  F04D19/005 ,  F04D25/066 ,  F04D25/08 ,  F04D29/325 ,  F04D29/526

Abstract: An axial fan includes a rotatable fan blade assembly including a plurality of fan blades, and a plurality of permanent magnets affixed to the plurality of fan blades. A stationary guide channel is located radially outboard of the fan blade assembly. A plurality of field coils are located at the guide channel and are configured to drive rotation of the fan blade assembly via magnetic interaction with the plurality of permanent magnets when the plurality of field coils are sequentially energized. A method of operating an axial fan includes energizing a plurality of field coils, urging a fan blade assembly out of contact with the guide channel via magnetic interaction between the plurality of field coils and a plurality of permanent magnets located at the fan blade assembly, and sequentially pulsing the plurality of field coils thereby urging rotation of the fan blade assembly about an axis of rotation.

公开(公告)号：US20170234315A1

公开(公告)日：2017-08-17

申请号：US15044316

申请日：2016-02-16

Applicant: Omar Hammoud

Inventor： Omar Hammoud

IPC: F04D25/02 ,  F02C6/18 ,  F04D29/22 ,  F02C7/36 ,  F01D5/02 ,  F04D29/28

CPC classification number: F04D25/02 ,  F01D15/005 ,  F01D15/10 ,  F02C3/04 ,  F02C3/10 ,  F02C3/22 ,  F02C6/18 ,  F04D13/04 ,  F04D25/04 ,  F05D2220/32 ,  F05D2220/62 ,  F05D2240/35 ,  Y02E20/14 ,  Y02T50/678

Abstract: A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporative cooling from using the remaining waste heat in the exhaust gas.

公开(公告)号：US20170218975A1

公开(公告)日：2017-08-03

申请号：US15009868

申请日：2016-01-29

Applicant: United Technologies Corporation

Inventor： Matthew E. Bintz ,  Frederick M. Schwarz ,  Yuan Dong

IPC: F04D29/36 ,  F04D29/52 ,  F04D25/02 ,  F04D29/56 ,  F02K3/06 ,  F01D5/02 ,  F04D25/04 ,  F04D19/00 ,  F02K1/72

CPC classification number: F02K1/72 ,  F01D7/00 ,  F02K1/09 ,  F04D25/028 ,  F04D29/323 ,  F05D2260/40311 ,  F05D2260/70 ,  F05D2260/74 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades rotatable about an engine axis. Each of the fan blades have a leading edge and rotate about a fan blade axis. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US09714662B2

公开(公告)日：2017-07-25

申请号：US13578838

申请日：2011-02-17

Applicant: Kazuaki Kurihara

Inventor： Kazuaki Kurihara

IPC: F04D25/02 ,  F04D17/12 ,  F04D25/06 ,  F04D29/62 ,  F04D25/16

CPC classification number: F04D25/02 ,  F04D17/122 ,  F04D25/06 ,  F04D25/0606 ,  F04D25/163 ,  F04D29/624

Abstract: Provided is a turbocompressor (4) having a drive part (12) generating rotational power, an impeller (22a) to which the rotational power of the drive part (12) is transmitted to rotate, a plurality of gears (31, 32) transmitting the rotational power of the drive part (12) to the impeller (22a), and a drive part casing (13) in which the drive part (12) is installed. This turbocompressor (4) includes an impeller casing (22e) installed around the impeller (22a), and a gear casing (33) configured to be formed independently of the impeller casing (22e) and the drive part casing (13), to couple the impeller casing (22e) and the drive part casing (13), and to form an accommodation space (33a) in which the plurality of gears (31, 32) are accommodated. With this configuration, in manufacturing the turbocompressor, a working process can be simplified and working labor and cost can be reduced.

公开(公告)号：US09695822B2

公开(公告)日：2017-07-04

申请号：US14489300

申请日：2014-09-17

Applicant: Ford Global Technologies, LLC

Inventor： James Douglas Ervin ,  August Thomas Vaught

IPC: F01D7/00 ,  F04C28/18 ,  F01D11/08 ,  F04D15/00 ,  F04D27/00 ,  F01D11/22 ,  F04D25/04 ,  F04D25/02 ,  F01D17/14 ,  F01D25/24 ,  F02B37/02 ,  F02B37/22 ,  F02B39/14 ,  F02B47/08 ,  F04C18/02

CPC classification number: F04C28/185 ,  F01D11/08 ,  F01D11/22 ,  F01D17/141 ,  F01D17/143 ,  F01D25/24 ,  F02B37/025 ,  F02B37/22 ,  F02B39/14 ,  F02B47/08 ,  F04C18/02 ,  F04D15/0033 ,  F04D25/024 ,  F04D25/045 ,  F04D27/002 ,  F04D27/0246 ,  F05D2220/40 ,  F05D2250/40 ,  Y02T10/144

Abstract: A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.

公开(公告)号：US20170175767A1

公开(公告)日：2017-06-22

申请号：US14974138

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  David A. Welch

IPC: F04D29/52 ,  F04D29/66 ,  F02K3/06 ,  F02C3/04 ,  F02C7/36 ,  F04D19/00 ,  F04D25/02

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.

公开(公告)号：US09624934B2

公开(公告)日：2017-04-18

申请号：US13688808

申请日：2012-11-29

Applicant: Cummins Ltd.

Inventor： John F Parker

IPC: F04D19/00 ,  F04D25/06 ,  F04D25/02 ,  F02B39/10

CPC classification number: F04D19/00 ,  F02B39/10 ,  F04D25/024 ,  F04D25/0606

Abstract: A turbocharger arrangement comprises a turbocharger and a generator. The turbocharger comprises a turbine having a turbine wheel and a compressor having a compressor wheel. The turbine wheel and the compressor wheel are mounted to a shaft, the shaft being supported by a bearing assembly located in a bearing housing between the turbine and the compressor, such that the shaft may rotate about an axis; The compressor wheel is between the generator and the bearing assembly; and an inducer portion of the compressor wheel is between an exducer portion of the compressor wheel and the bearing assembly.