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公开(公告)号：US11994149B2
公开(公告)日：2024-05-28
申请号：US18033922
申请日：2021-10-25
申请人： Xylem Europe GmbH
发明人： Viktor Bredwad , Stefan Ramström
CPC分类号： F04D29/4293 , F04D29/708 , F05D2250/51
摘要： An impeller seat for a pump, the impeller seat comprising an inlet wall, an inlet radius, a guide pin connected to and extending radially inwards from the inlet wall. The guide pin includes a tip radius. A 15%-circle is offset radially inwards from a circular intersection fifteen percent of the difference between the inlet radius and the tip radius. An 85%-circle is offset radially inwards from the circular intersection eighty-five percent of the difference between the inlet radius and the tip radius. A trailing edge line is between the intersection between the 15%-circle and a trailing edge of the guide pin and the intersection between the 85%-circle and the trailing edge of the guide pin. The trailing edge line is in a range equal to or more than 10 degrees and equal to or less than 30 degrees.
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公开(公告)号：US11976667B2
公开(公告)日：2024-05-07
申请号：US17439141
申请日：2019-03-19
发明人： Kenichiro Iwakiri , Isao Tomita , Masaki Tojo , Takashi Yoshimoto
CPC分类号： F04D29/4213 , F04D25/024 , F04D29/464 , F05D2220/40 , F05D2250/51
摘要： A centrifugal compressor comprises: an impeller; an inlet pipe portion forming an intake passage to introduce air to the impeller; and a throttle mechanism capable of reducing a flow passage area of the intake passage upstream of the impeller. The throttle mechanism includes an annular portion configured to move between a first position and a second position upstream of the first position in an axial direction of the impeller. In a cross-section along a rotational axis of the impeller, an outer peripheral surface of the annular portion is formed to smoothly connect a leading edge and a trailing edge of the annular portion.
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公开(公告)号：US11919654B2
公开(公告)日：2024-03-05
申请号：US17817749
申请日：2022-08-05
发明人： Eray Akcayoz
CPC分类号： B64D33/02 , F02C7/042 , B64D2033/0293 , F05D2220/323 , F05D2250/51
摘要： An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.
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公开(公告)号：US11713692B2
公开(公告)日：2023-08-01
申请号：US16015599
申请日：2018-06-22
发明人： Thomas Dewey Parsons
CPC分类号： F01D21/003 , B64D43/00 , F02C7/055 , G07C5/006 , G07C5/0808 , G07C5/0825 , F05D2220/329 , F05D2250/51 , F05D2260/80
摘要： A differential pressure transducer provides measurements for determining the restriction, updated in real time, of an inlet barrier filter for a turboshaft engine of an aircraft. The percentage of restriction of the air inlet barrier filter, which corresponds to the condition of the air inlet barrier filter, is determined as a function of mass air flow into the engine during operation. The restriction percentage is indicated on the instrument panel of the rotorcraft.
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公开(公告)号：US20190242291A1
公开(公告)日：2019-08-08
申请号：US16339357
申请日：2017-09-01
发明人： Johannes Diekmann , Thorsten Grelle , Michael Krappel , Gunnar Schmitt-Sauter , Benjamin Weimann
CPC分类号： F01P5/10 , F04D29/4293 , F05D2250/51
摘要： A liquid pump for conveying a liquid may include a housing, in which a pump impeller is arranged for conveying the liquid, and a cover for covering the housing. The cover may include a main connector for supplying a main flow of the liquid to the pump impeller and an auxiliary connector for supplying an auxiliary flow of the liquid to the pump impeller. The housing may have an inlet opening for the liquid and an annular collar protruding from an edge of the inlet opening. The cover may lie axially against the annular collar. The annular collar and the cover may define an annular wall surrounding a flow path of the main flow of the liquid. The annular wall may have at least one radial opening connecting the flow path with an inflow space surrounding the annular wall. The auxiliary connector may be fluidically connected with the inflow space.
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公开(公告)号：US20190162118A1
公开(公告)日：2019-05-30
申请号：US16264837
申请日：2019-02-01
CPC分类号： F02C7/18 , B64D2013/0603 , F01D25/12 , F02C6/08 , F02C9/18 , F02K3/06 , F02K3/062 , F05D2220/324 , F05D2220/327 , F05D2250/51 , Y02T50/675
摘要： A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
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公开(公告)号：US20190078587A1
公开(公告)日：2019-03-14
申请号：US15700995
申请日：2017-09-11
CPC分类号： F04D29/464 , F02B37/24 , F04D27/002 , F04D27/0215 , F04D27/0246 , F04D29/4206 , F04D29/462 , F04D29/681 , F05D2220/40 , F05D2250/51
摘要： 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.
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公开(公告)号：US20180163731A1
公开(公告)日：2018-06-14
申请号：US15839971
申请日：2017-12-13
CPC分类号： F04D17/10 , F02B33/40 , F02B37/225 , F04D29/284 , F04D29/4213 , F04D29/444 , F04D29/685 , F05D2220/40 , F05D2250/51 , Y02T10/144
摘要： A centrifugal compressor includes a rotary blade that is rotatable around an axis. The centrifugal compressor includes an inlet part that extends in the axial direction, that forms an inlet passage to introduce gas to the rotary blade, and that includes a circular cross section. The centrifugal compressor includes a projecting part that projects from a part of a circumferential wall surface of the inlet passage. A top end of the projecting part is located within an inflow region through which gas flows to the rotary blade. An inclined surface of the projecting part is formed to be inclined so that the top end of the projecting part is located downstream in a rotation direction of the rotary blade relative to a base end of the projecting part.
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公开(公告)号：US20180135514A1
公开(公告)日：2018-05-17
申请号：US15276904
申请日：2016-09-27
发明人： Dinesh Venugopal Setty , Richard Lynn Loud , Pramod Akulu , Haribalakrishnan Sankarakumar , Shubhra Bhatnagar , Laxmikant Merchant
CPC分类号： F02C7/045 , F02C7/24 , F05D2240/14 , F05D2250/232 , F05D2250/51 , F05D2260/96 , F05D2260/963
摘要： The present disclosure is directed to a sound attenuation system for a gas turbine engine. The sound attenuation system includes a compressor inlet casing having a compressor inlet casing inner surface and defining a compressor inlet passage extending therethrough. An inlet plenum body couples to the compressor inlet casing. The inlet plenum body includes an inlet body inner surface and defines an inlet plenum therein. One or more sound attenuating panels couple to at least one of the compressor inlet casing inner surface and the inlet plenum body inner surface of the duct. Each sound attenuating panel includes a first sheet defining a first plurality of apertures extending therethrough and a solid second sheet spaced apart from the first sheet.
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公开(公告)号：US20180106193A1
公开(公告)日：2018-04-19
申请号：US15292203
申请日：2016-10-13
CPC分类号： F02C3/04 , F01D17/162 , F02C3/10 , F02C3/145 , F05D2250/51 , F05D2250/80 , F05D2300/6033 , F23R3/54 , Y02T50/672
摘要： A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 2,000 horsepower during peak operations. The compressor section defines an overall compressor ratio of at least 15:1 in order to increase in overall efficiency of the gas turbine engine.
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