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公开(公告)号：US20190003325A1
公开(公告)日：2019-01-03
申请号：US15416144
申请日：2017-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Paul Couey , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
Abstract: A turbine section of a gas turbine engine is provided. The turbine section includes a first turbine with a first inlet and a first outlet; second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least two splitter blades disposed within the inter-turbine duct. The at least two splitter blades include a first splitter blade and a second splitter blade radially interior to the first splitter blade. At least the second splitter blade has a radial position that is greater than 60% of a distance from the shroud to the hub.
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Patent Agency Ranking
公开(公告)号：US09400110B2
公开(公告)日：2016-07-26
申请号：US13656219
申请日：2012-10-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Terrel Kuhn , Vinayender Kuchana , Veeraraghava Raju Hasti , Raymond Gage , Sunil James
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/54 , F23R2900/00015 , F23R2900/03041 , Y02T50/675
Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和连接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。
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公开(公告)号：US20190136702A1
公开(公告)日：2019-05-09
申请号：US15808214
申请日：2017-11-09
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
IPC: F01D9/04
Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.
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公开(公告)号：US20140109581A1
公开(公告)日：2014-04-24
申请号：US13656219
申请日：2012-10-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Terrel Kuhn , Vinayender Kuchana , Veeraraghava Raju Hasti , Raymond Gage , Sunil James
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/54 , F23R2900/00015 , F23R2900/03041 , Y02T50/675
Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和联接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。
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公开(公告)号：US20200240278A1
公开(公告)日：2020-07-30
申请号：US16677020
申请日：2019-11-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.
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公开(公告)号：US11131205B2
公开(公告)日：2021-09-28
申请号：US16677020
申请日：2019-11-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.
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