公开(公告)号：US10590944B2

公开(公告)日：2020-03-17

申请号：US15726273

申请日：2017-10-05

Applicant: Ford Global Technologies, LLC

Inventor： Leon Hu ,  Jianwen James Yi

IPC: F04D27/02 ,  F04D29/58 ,  F04D29/42 ,  F04D29/68 ,  F04D17/10 ,  F04D27/00 ,  F04D29/28

Abstract: Methods and systems are provided for cooling a compressor in an engine. In one example, a compressor with a liquid coolant passage extending through a section of a housing of the compressor adjacent to a bypass passage, is provide. The bypass passage enable airflow to be directed around a portion of a compressor impeller.

公开(公告)号：US10584719B2

公开(公告)日：2020-03-10

申请号：US15700995

申请日：2017-09-11

Applicant: Ford Global Technologies, LLC

Inventor： Tao Zeng ,  Leon Hu

IPC: F04D29/46 ,  F02B37/24 ,  F04D27/02 ,  F04D27/00 ,  F04D29/42 ,  F04D29/68

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include a casing forming a recirculation passage surrounding an intake passage, an active casing treatment surrounding a wall separating the intake passage and the recirculation passage and adapted to selectively control a flow of gas through a plurality of ports disposed in the wall, and an impeller. Additionally, a variable inlet device may be position in the intake passage, upstream of the impeller, the variable inlet device including a plurality of adjacently arranged blades forming a ring, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

公开(公告)号：US10480531B2

公开(公告)日：2019-11-19

申请号：US15220451

申请日：2016-07-27

Applicant: Mitsubishi Hitachi Power Systems, Ltd.

Inventor： Takanori Shibata ,  Naoto Omura ,  Chihiro Myoren ,  Yasuo Takahashi

IPC: F01D5/14 ,  F04D29/54 ,  F04D29/32 ,  F04D29/52 ,  F04D19/02 ,  F04D29/68

Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion. Each blade of the blade row located at the protruding portion of the wall surface is configured such that an increase rate in a wall surface direction of a blade outlet angle in a blade end portion on the side of the wall surface having the protruding portion is greater than an increase rate in the wall surface direction of a blade outlet angle in a blade height intermediate portion.

公开(公告)号：US20190323356A1

公开(公告)日：2019-10-24

申请号：US16462327

申请日：2017-11-17

Applicant: Dyson Technology Limited

Inventor： Qiang LIU ,  Shan ZHONG ,  Mark Andrew JOHNSON ,  Matthieu Michel Xavier DE MAILLARD

IPC: F01D5/14 ,  B64C21/10 ,  F04D29/32 ,  F04D29/38 ,  F04D29/68 ,  F15D1/00 ,  F15D1/12

Abstract: A compressor blade having a leading edge and a trailing edge, and a surface pattern between the leading and trailing edges, the surface pattern comprising at least one set of herringbone riblets formed of a plurality of v-shaped riblets, wherein the v-shaped riblets are spaced apart by a distance of between 200-400 μm, and have a height of between 50-120 μm.

公开(公告)号：US10436218B2

公开(公告)日：2019-10-08

申请号：US15314379

申请日：2014-07-03

Applicant: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER , LTD.

Inventor： Makoto Ozaki ,  Hiroshi Suzuki ,  Koji Wakashima ,  Isao Tomita ,  Tadashi Kanzaka

IPC: F04D17/10 ,  F04D29/42 ,  F04D29/62 ,  F04D29/68 ,  F04D29/66 ,  F04D29/44 ,  F04D27/02 ,  F02B33/40 ,  F02B37/00

Abstract: A compressor cover covering a delivery fan radially outwardly discharging a fluid from an axial direction by rotating around the axis, the compressor cover comprising: a cover body including a tubular part in which a tubular inner peripheral surface along the axis and a shroud surface disposed on an axially downstream side of the tubular inner peripheral surface and expands in diameter toward the downstream side are formed; and a sleeve including an outer tube having an outer peripheral surface fitted to the tubular inner peripheral surface, an inner tube disposed on a radially inner side of the outer tube and defines a recirculation flow path in which a portion of the fluid circulates between the inner tube and the outer tube, and a plurality of struts disposed at intervals in the peripheral direction.

公开(公告)号：US10371050B2

公开(公告)日：2019-08-06

申请号：US14928504

申请日：2015-10-30

Applicant: Rolls-Royce Corporation

Inventor： Benjamin M. Iwrey

IPC: F01D11/20 ,  F02C7/04 ,  F01D11/08 ,  F04D29/16 ,  F04D29/68 ,  F01D5/20

Abstract: A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors. Each rotor includes a number of blades radially extending from a rotor wheel and terminating in a blade tip. The blade tip terminates in close proximity to the case and defines a tip clearance. An air flow control system is coupled to the compressor. The air flow system includes inductive coils and plasma actuators coupled to the case and magnets coupled to the blade. The plasma actuators induce air flows in order to, for example, mitigate air flow leakage around the tip of the blade.

公开(公告)号：US10364825B2

公开(公告)日：2019-07-30

申请号：US15468278

申请日：2017-03-24

Applicant: IHI Corporation

Inventor： Yasutaka Bessho

IPC: F04D29/44 ,  F04D17/10 ,  F04D29/28 ,  F04D29/42 ,  F02B39/00 ,  F04D29/68 ,  F02B33/40 ,  F02B37/00

Abstract: A centrifugal compressor includes a flow changing groove that is formed on an inner wall of the suction passage and extends in a rotation direction of the compressor wheel. A boundary part of a groove wall of the flow changing groove and the inner wall of the suction passage includes an upstream boundary part positioned on an upstream side in the circulation direction of the gas, and a downstream boundary part positioned on a downstream side in the circulation direction. The upstream boundary part is positioned on the inner side in a radial direction of the compressor wheel than the downstream boundary part, and the flow changing groove is positioned on the upstream side of the wheel in the circulation direction.

公开(公告)号：US20190226501A1

公开(公告)日：2019-07-25

申请号：US16252996

申请日：2019-01-21

Applicant: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI

Inventor： Tatsuya ARAKAWA ,  Hidetoshi HARIMA ,  Shuichi HIROTA ,  Yutaka YAMAGUCHI ,  Kazushige MURAO

IPC: F04D29/68 ,  F04D29/42 ,  F02B37/18

Abstract: A turbocharger includes a compressor housing having an accommodation depression, a return passage, a ring member, and a covering member mounted to the compressor housing. The return passage has an inlet, an outlet, and a communication passage through which the inlet is connected to the outlet. A bottom surface of the accommodation depression has an inlet forming surface that cooperates with the ring member to form the inlet. The communication passage is formed between an inner peripheral surface of the accommodation depression and an outer peripheral surface of the ring member. The covering member has a falling prevention portion and an outlet forming surface. The outlet forming surface cooperates with the ring member to form the outlet. The falling prevention portion is located between the ring member and the outlet forming surface, and contacts the ring member to prevent the ring member from falling off the accommodation depression.

公开(公告)号：US10359054B2

公开(公告)日：2019-07-23

申请号：US15184692

申请日：2016-06-16

Applicant: Techspace Aero S.A.

Inventor： Stéphane Hiernaux

IPC: F04D29/68 ,  F04D27/02 ,  F04D29/52 ,  F01D11/04 ,  F01D11/14 ,  F01D11/10

Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

公开(公告)号：US10358931B2

公开(公告)日：2019-07-23

申请号：US15415498

申请日：2017-01-25

Applicant: Rolls-Royce plc

Inventor： Chaitanya Paruchuri ,  Philip Joseph ,  Jae-Wook Kim

IPC: F01D9/04 ,  B64C3/14 ,  B64C11/18 ,  B63H1/26 ,  F01D5/14 ,  F04D29/32 ,  F04D29/68 ,  F04D29/54

Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.