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公开(公告)号：US10316671B2
公开(公告)日：2019-06-11
申请号：US14802512
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
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公开(公告)号：US11994089B2
公开(公告)日：2024-05-28
申请号：US16837143
申请日：2020-04-01
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis
CPC classification number: F02K3/06 , F04D29/323 , F01D17/162 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/12 , F05D2240/35 , F05D2260/40311 , F05D2260/74 , F05D2260/79
Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.
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3.发明申请公开(公告)号：US20160024935A1
公开(公告)日：2016-01-28
申请号：US14802512
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
CPC classification number: F01D5/18 , F01D5/141 , F01D5/147 , F01D5/28 , F05D2230/211 , F05D2300/1723 , Y02T50/673
Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
Abstract translation: 用于燃气涡轮发动机的叶片包括主体，该主体包括翼型件，该翼型件在翼型基座附近的0％跨度位置处沿径向方向延伸到翼型端部处的100％跨度位置。 翼型件包括具有第一密度的翼型底座附近的第一部分，并且包括具有第二密度的翼型末端附近的第二部分。 第二密度小于第一密度。 第二部分包括在径向方向上增加的真弦长度。
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公开(公告)号：US20210262359A1
公开(公告)日：2021-08-26
申请号：US16797194
申请日：2020-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis , Nathan L. Messersmith
IPC: F01D15/10 , F02C6/06 , F01D15/12 , H02K7/116 , H02K7/18 , H02K7/20 , H02K11/00 , B64D27/10 , B64D27/24 , B64D41/00
Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.
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Patent Agency Ranking
公开(公告)号：US20200024962A1
公开(公告)日：2020-01-23
申请号：US16397265
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.
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公开(公告)号：US11846196B2
公开(公告)日：2023-12-19
申请号：US16797194
申请日：2020-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis , Nathan L. Messersmith
IPC: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/18 , H02K7/20 , H02K11/00 , B64D27/02
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/1823 , H02K7/20 , H02K11/0094 , B64D2027/026 , F05D2220/50 , F05D2220/76
Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.
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公开(公告)号：US10954799B2
公开(公告)日：2021-03-23
申请号：US16397265
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.
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公开(公告)号：US20200325852A1
公开(公告)日：2020-10-15
申请号：US16837143
申请日：2020-04-01
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis
Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.
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公开(公告)号：US20170335712A1
公开(公告)日：2017-11-23
申请号：US15161436
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , Eric A. Grover , John D. Teixeira
CPC classification number: F01D17/162 , F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2250/35 , F05D2250/90 , Y02T50/673
Abstract: Airfoils are provided having a body having a leading edge, a trailing edge, a first end surface, and a second end surface opposite the first end surface, wherein (i) a first true chord length is a line extending from a first leading edge point to a first trailing edge point and (ii) a second true chord length is a line extending from a second leading edge point to a second trailing edge point, a first button located on the first end surface of the airfoil body, the first button having a first diameter and a first attachment device extending from the first button to enable rotation of the airfoil body about an attachment device axis. The first diameter is at least 15% of the first true chord length or the attachment device axis is located 10% of the first true chord length from the leading edge point.
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