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公开(公告)号：US20240328321A1
公开(公告)日：2024-10-03
申请号：US18127349
申请日：2023-03-28
发明人： Masoud Roshan Fekr , Rana Foroutan , Robert Huszar
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F05D2220/32 , F05D2230/60 , F05D2240/30 , F05D2260/83
摘要： A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.
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公开(公告)号：US11913356B2
公开(公告)日：2024-02-27
申请号：US17545415
申请日：2021-12-08
发明人： Chao Zhang , Robert Huszar , Othmane Leghzaouni
CPC分类号： F01D5/28 , C30B11/02 , C30B29/52 , F01D5/147 , F05D2230/50 , F05D2250/232 , F05D2300/607
摘要： A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.
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公开(公告)号：US10975714B2
公开(公告)日：2021-04-13
申请号：US16198827
申请日：2018-11-22
发明人： Daniel Lecuyer , Robert Huszar
摘要： The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.
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公开(公告)号：US12070811B2
公开(公告)日：2024-08-27
申请号：US17200988
申请日：2021-03-15
发明人： Daniel Lecuyer , Robert Huszar
CPC分类号： B23H9/10 , B23P15/008 , B23P15/04 , F01D5/3007 , F01D11/006 , F05D2230/12 , F05D2240/55 , F05D2240/80 , F05D2260/30 , Y10T29/4932 , Y10T29/49336
摘要： A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.
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公开(公告)号：US11572790B1
公开(公告)日：2023-02-07
申请号：US17454529
申请日：2021-11-11
发明人： Remo Marini , Panagiota Tsifourdaris , Nicolas Grivas , Daniel Lecuyer , Michael Papple , Robert Huszar , Othmane Leghzaouni , Jonathan Dorai , Jasrobin Grewal
摘要： A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
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公开(公告)号：US11220919B2
公开(公告)日：2022-01-11
申请号：US16515383
申请日：2019-07-18
发明人： Chao Zhang , Robert Huszar , Othmane Leghzaouni
摘要： A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.
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公开(公告)号：US10513929B2
公开(公告)日：2019-12-24
申请号：US15692388
申请日：2017-08-31
发明人： Niloofar Moradi , Krishan Mohan , Panagiota Tsifourdaris , Sami Girgis , Vincent Paradis , Robert Huszar , Jasrobin Grewal
摘要： A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
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