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公开(公告)号：US10816014B2
公开(公告)日：2020-10-27
申请号：US16044704
申请日：2018-07-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , John Schugardt , Mahmoud Mansour , Richard Bonvouloir
Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.
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公开(公告)号：US20180306203A1
公开(公告)日：2018-10-25
申请号：US15497186
申请日：2017-04-25
Applicant: Honeywell International Inc.
Inventor： Shakeel Nasir , Hasham Hamzamiyan Chougule , Amarnath Balu Rajan
CPC classification number: F04D29/444 , F01D9/045 , F02C6/12 , F02C7/08 , F04D17/105 , F04D29/285 , F04D29/4206 , F05D2220/40
Abstract: A compressor assembly of a turbocharger can include a compressor housing that includes a compressor wheel space and a diffuser section that extends from the compressor wheel space to at least one volute; a dual-faced compressor wheel disposed at least in part in the compressor wheel space where the dual-faced compressor wheel includes a first compressor wheel face and a second compressor wheel face oriented back-to-back; and a diffuser section divider disposed at least in part in the diffuser section where the diffuser section divider includes a first side that defines in part a first diffuser that includes a first set of vanes associated with the first compressor wheel face and a second side that defines in part a second diffuser that includes a second set of vanes associated with the second compressor wheel face.
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公开(公告)号：US20180135516A1
公开(公告)日：2018-05-17
申请号：US15352839
申请日：2016-11-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Yogendra Yogi Sheoran , John Schugardt , Daniel Aukland , Mahmoud Mansour , Cristopher Frost , Matt Greenman
IPC: F02C7/052
CPC classification number: F02C7/052 , F02C3/04 , F02C7/00 , F04D29/444 , F04D29/701 , F05D2250/52 , F05D2260/607 , Y02T50/675
Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.
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公开(公告)号：US20170284226A1
公开(公告)日：2017-10-05
申请号：US15085625
申请日：2016-03-30
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , John Schugardt , Nick Nolcheff , John Meier , Yogendra Yogi Sheoran , Shezan Kanjiyani , Daniel Aukland
IPC: F01D25/32
CPC classification number: F01D25/32 , F02C7/36 , F04D29/441 , F04D29/701 , F05D2220/32 , F05D2250/52 , F05D2260/40311 , F05D2260/607 , Y02T50/675
Abstract: A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.
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公开(公告)号：US11732731B2
公开(公告)日：2023-08-22
申请号：US17450306
申请日：2021-10-08
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Song Xue , Raymond Mccage , Jeffrey Krise , Shakeel Nasir , Joseph Becar
CPC classification number: F04D29/441 , F04D17/10 , F04D29/667
Abstract: A diffuser and deswirl system associated with an engine includes a throat ring defining a plurality of passages spaced apart about a perimeter of the throat ring, a plurality of pockets and a support flange. Each passage of the plurality of passages is to receive a working fluid and each pocket of the plurality of pockets is defined about a portion of a respective passage of the plurality of passages. The diffuser and deswirl system includes a plurality of conduits, with each conduit including a first conduit end and a second conduit end opposite the first conduit end. The first conduit end of each conduit is received within and coupled to the pocket of a respective one of the plurality of passages to receive the working fluid, and each conduit includes a mating feature defined between the first conduit end and the second conduit end coupled to the support flange.
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Patent Agency Ranking
公开(公告)号：US20210079929A1
公开(公告)日：2021-03-18
申请号：US16951258
申请日：2020-11-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Nick Nolcheff , Cristopher Frost
IPC: F04D29/44
Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.
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公开(公告)号：US20200248712A1
公开(公告)日：2020-08-06
申请号：US16266484
申请日：2019-02-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Nick Nolcheff , Cristopher Frost
Abstract: Circumferentially-split diffuser assemblies utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the diffuser assembly includes flow passages, which extend through the diffuser assembly and which include diffuser flow passage sections. Diffuser airfoils are interspersed with the diffuser flow passage sections. The diffuser airfoils include inboard and outboard airfoil segments distributed around a diffuser assembly centerline. The inboard and outboard airfoil segments are contained in and, thus, defined by inner and outer annular diffuser structures, respectively. The outer annular diffuser structure circumscribes the inner annular diffuser structure. In certain cases, the inboard airfoil segments and at least a portion of inner annular diffuser structure are composed of a first material, while the outboard airfoil segments and at least a portion of outboard annular diffuser structure are composed of a second material different than the first material.
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公开(公告)号：US20200166049A1
公开(公告)日：2020-05-28
申请号：US16201699
申请日：2018-11-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Nick Nolcheff , Cristopher Frost
IPC: F04D29/44
Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.
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公开(公告)号：US20200032818A1
公开(公告)日：2020-01-30
申请号：US16044704
申请日：2018-07-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , John Schugardt , Mahmoud Mansour , Richard Bonvouloir
Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.
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公开(公告)号：US20170362947A1
公开(公告)日：2017-12-21
申请号：US15183274
申请日：2016-06-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , John Schugardt , Justin Brown , Cristopher Frost
IPC: F01D9/06 , F04D17/02 , F04D29/54 , F04D29/28 , F02C3/04 , F04D29/42 , F04D29/32 , F04D29/44 , F04D29/52
Abstract: Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.
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