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公开(公告)号：US10378453B2
公开(公告)日：2019-08-13
申请号：US14844097
申请日：2015-09-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Julian Partyka , David R. Pack , James D. Hill
Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.
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12.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：US11952911B2
公开(公告)日：2024-04-09
申请号：US16683640
申请日：2019-11-14
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack , JinQuan Xu
IPC: F01D5/18
CPC classification number: F01D5/18 , F05D2220/32 , F05D2240/304 , F05D2260/22141
Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.
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Patent Agency Ranking
公开(公告)号：US11480059B2
公开(公告)日：2022-10-25
申请号：US16545417
申请日：2019-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.
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公开(公告)号：US11149550B2
公开(公告)日：2021-10-19
申请号：US16270080
申请日：2019-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , David R. Pack
Abstract: A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.
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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：US10378364B2
公开(公告)日：2019-08-13
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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公开(公告)号：US20190136699A1
公开(公告)日：2019-05-09
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
CPC classification number: F01D5/187 , F01D5/186 , F01D5/188 , F02C7/18 , F04D29/324 , F04D29/542 , F05D2220/323 , F05D2240/126 , F05D2240/301 , F05D2250/11 , F05D2250/131 , F05D2260/22141
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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