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公开(公告)号：US20230111022A1
公开(公告)日：2023-04-13
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
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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公开(公告)号：US12006879B1
公开(公告)日：2024-06-11
申请号：US18170161
申请日：2023-02-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , John McClintic , Jeffrey Krise
IPC: F02C9/18
CPC classification number: F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/60
Abstract: A bleed arrangement for a turbomachine that results in uniform flow to the combustor. A turbomachine includes a compressor, a combustor disposed to receive the compressed air from the compressor through a flow path, and a diffuser disposed in the flow path between the compressor and the combustor. A number of bleed holes are disposed downstream in the flow path from the diffuser and are configured to direct bleed air compressed by the compressor away from the combustor. The number of bleed holes have a plural number of sizes configured to provide uniform compressor exit flow distribution around a circumference of the diffuser.
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公开(公告)号：US11333171B2
公开(公告)日：2022-05-17
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：US10989219B2
公开(公告)日：2021-04-27
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：US20200049069A1
公开(公告)日：2020-02-13
申请号：US16656262
申请日：2019-10-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Yogendra Yogi Sheoran , John Schugardt , Daniel Aukland , Mahmoud Mansour , Cristopher Frost , Matt Greenman
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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Patent Agency Ranking
公开(公告)号：US11421595B2
公开(公告)日：2022-08-23
申请号：US16656262
申请日：2019-10-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Yogendra Yogi Sheoran , John Schugardt , Daniel Aukland , Mahmoud Mansour , Cristopher Frost , Matt Greenman
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 flowpath, 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 in operation, but does not occur continuously during engine operation.
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公开(公告)号：US10544693B2
公开(公告)日：2020-01-28
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 , F04D29/44 , F02C3/04 , F04D17/02 , F04D29/28 , F04D29/32 , F04D29/42 , F04D29/52 , F04D29/54 , F01D9/04
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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公开(公告)号：US10208628B2
公开(公告)日：2019-02-19
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
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：US11959401B1
公开(公告)日：2024-04-16
申请号：US18189739
申请日：2023-03-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Atul Verma , Jeffrey Krise , Doni Tapederi , Jacob Salai , Rodolphe Dudebout
CPC classification number: F01D9/04 , F02C3/04 , F23R3/26 , F05D2220/323 , F05D2240/127 , F05D2260/60
Abstract: A deswirl system for a gas turbine engine includes a deswirl shroud, and at least one deswirl vane having a leading end and a trailing end. The deswirl system includes a deswirl hub spaced apart from the deswirl shroud by the at least one deswirl vane. The deswirl hub includes a hub body that extends at a first angle and a hub extension that extends beyond the trailing end of the at least one deswirl vane. The hub extension extends from the hub body at a second angle, and the first angle is different than the second angle.
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公开(公告)号：US11506059B2
公开(公告)日：2022-11-22
申请号：US17030040
申请日：2020-09-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shailesh Kumar , Shakeel Nasir , Jyotichandra Jingade , Mahmoud Mansour
Abstract: An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.
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