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公开(公告)号：US08684668B1
公开(公告)日：2014-04-01
申请号：US13685053
申请日：2012-11-26
Applicant: Russell B Jones , Judson J Krueger , William L Plank
Inventor： Russell B Jones , Judson J Krueger , William L Plank
IPC: F01D9/04
CPC classification number: F01D5/188 , F01D9/04 , F01D9/065 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/191 , F05D2260/201 , Y02T50/676
Abstract: A sequential impingement cooling insert for a turbine stator vane that forms a double impingement for the pressure and suction sides of the vane or a triple impingement. The insert is formed from a sheet metal formed in a zigzag shape that forms a series of alternating impingement cooling channels with return air channels, where pressure side and suction side impingement cooling plates are secured over the zigzag shaped main piece. Another embodiment includes the insert formed from one or two blocks of material in which the impingement channels and return air channels are machined into each block.
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公开(公告)号：US10208619B2
公开(公告)日：2019-02-19
申请号：US15174051
申请日：2016-06-06
Applicant: Russell B Jones , Barry J Brown , Stephen E Murray
Inventor： Russell B Jones , Barry J Brown , Stephen E Murray
IPC: F01D17/16
Abstract: A turbine with a variable inlet guide vane assembly in which the vane airfoils extend between inner and outer buttons, and in which a center of rotation of the airfoil is located aft of an aerodynamic center of pressure of the airfoil. The trailing edge of the airfoil extends into both of the buttons such that no gap is formed between the airfoil trailing edge region and a static part of the turbine during movement of the airfoil from an opened position to a closed position.
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公开(公告)号：US20170234152A1
公开(公告)日：2017-08-17
申请号：US15174051
申请日：2016-06-06
Applicant: Russell B Jones , Barry J Brown , Stephen E Murray
Inventor： Russell B Jones , Barry J Brown , Stephen E Murray
CPC classification number: F01D17/162
Abstract: A turbine with a variable inlet guide vane assembly in which the vane airfoils extend between inner and outer buttons, and in which a center of rotation of the airfoil is located aft of an aerodynamic center of pressure of the airfoil. The trailing edge of the airfoil extends into both of the buttons such that no gap is formed between the airfoil trailing edge region and a static part of the turbine during movement of the airfoil from an opened position to a closed position.
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公开(公告)号：US10151211B2
公开(公告)日：2018-12-11
申请号：US14854119
申请日：2015-09-15
Applicant: Joseph D Brostmeyer , Russell B Jones
Inventor： Joseph D Brostmeyer , Russell B Jones
Abstract: An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.
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公开(公告)号：US10006293B1
公开(公告)日：2018-06-26
申请号：US14805918
申请日：2015-07-22
Applicant: Russell B Jones
Inventor： Russell B Jones
IPC: F01D5/18 , B22F5/04 , B22F7/08 , B22F3/105 , F01D25/12 , B23P15/02 , B23K15/00 , B33Y80/00 , B33Y10/00 , F01D5/00
CPC classification number: F01D5/186 , B22F3/1055 , B22F5/04 , B22F7/06 , B22F7/08 , B22F2005/103 , B22F2999/00 , B23K15/0086 , B23P15/02 , B23P15/04 , B23P2700/06 , B33Y10/00 , B33Y80/00 , F01D5/005 , F01D25/12 , F05D2220/32 , F05D2230/22 , F05D2230/233 , F05D2230/237 , F05D2230/30 , F05D2250/25 , F05D2250/71 , F05D2260/202 , F05D2300/131 , Y02P10/295 , B22F2201/03
Abstract: A part formed using an metal additive manufacturing process such as a turbine airfoil with an oversized feature such as an oversized hole, where the oversized hole is filled with a preform having a shape of a normal sized hole and secured within the part using a braze or weld material, and where the preform is removed to leave within the part the normal sized hole. The preform is made of a refractory material that can be removed from the part by exposure to oxygen.
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Patent Agency Ranking
公开(公告)号：US09683444B1
公开(公告)日：2017-06-20
申请号：US14561676
申请日：2014-12-05
Applicant: Russell B Jones
Inventor： Russell B Jones
CPC classification number: F01D5/188 , F01D5/187 , F01D9/023 , F01D9/041 , F01D9/065 , F05D2240/81 , F05D2260/201 , F05D2260/204 , F05D2260/205
Abstract: An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
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公开(公告)号：US09771821B1
公开(公告)日：2017-09-26
申请号：US14739536
申请日：2015-06-15
Applicant: Jacob A Mills , Russell B Jones , Thomas D Sexton
Inventor： Jacob A Mills , Russell B Jones , Thomas D Sexton
CPC classification number: F01D11/025 , F01D11/04 , F05D2240/511 , F05D2300/507 , F16J15/441 , F16J15/445 , F16J15/453
Abstract: An interstage seal for a turbine of a gas turbine engine, the interstage seal having a seal carrier with an axial extending seal tooth movable with a stator of the engine, and a rotor with a seal surface that forms the interstage seal with the seal tooth, where a magnetic force produced by two magnets and a gas force produced by a gas pressure acting on the seal carrier forms a balancing force to maintain a close clearance of the seal without the seal tooth contacting the rotor seal surfaces during engine operation. In other embodiments, two pairs of magnets produce first and second magnetic forces that balance the seal in the engine.
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公开(公告)号：US09581028B1
公开(公告)日：2017-02-28
申请号：US14291510
申请日：2014-05-30
Applicant: Russell B Jones , Alex Pinera
Inventor： Russell B Jones , Alex Pinera
CPC classification number: F01D5/18 , B22F3/1055 , B22F5/04 , B22F7/08 , B33Y10/00 , B33Y80/00 , F01D5/188 , F01D5/189 , F01D9/065 , F01D25/12 , Y02T50/676
Abstract: An air cooled turbine stator vane form a small gas turbine engine in which the vane has an airfoil of less than one inch in spanwise height, where the airfoil is a hollow airfoil having an insert that forms a sequential impingement cooling circuit for the pressure side wall and then the suction side wall. The insert includes a plurality of cooling air supply channels connected together by ribs where pressure side impingement holes are formed in the cooling air supply channels and suction side wall impingement cooling holes are formed in the ribs.
Abstract translation: 风冷式涡轮机定子叶片形成小型燃气涡轮发动机，其中叶片具有翼展高度小于1英寸的翼型，其中翼型是具有插入件的中空翼型件，该插入件形成用于压力侧壁的顺序冲击冷却回路 然后吸入侧壁。 插入件包括通过肋连接在一起的多个冷却空气供给通道，其中在冷却空气供应通道中形成有压力侧冲击孔，并且在肋中形成吸入侧壁冲击冷却孔。
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公开(公告)号：US09353687B1
公开(公告)日：2016-05-31
申请号：US14450944
申请日：2014-08-04
Applicant: Joseph D Brostmeyer , John W Appleby, Jr. , Russell B Jones
Inventor： Joseph D Brostmeyer , John W Appleby, Jr. , Russell B Jones
CPC classification number: F02C7/16 , F01D5/185 , F01D9/065 , F01D25/12 , F05B2260/205 , F05D2260/207 , F05D2260/232 , F05D2300/1606 , F05D2300/1612 , Y02T50/672 , Y02T50/676
Abstract: A gas turbine engine with a closed-loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes are made of a metallic material that will not react with the liquid metal cooling fluid. The stator vane may be made from a typical metal material such as ferrous metal alloys, nickel alloys or cobalt (Co) alloys, and an insert or liner made of molybdenum or tantalum may be placed inside to protect the outer vane material from reacting with a liquid metal such as bismuth, lead (Pb), indium, or alloy mixtures of thereof. In the case where the liquid coolant is bismuth, the liquid bismuth must be purged from the cooling system before the fluid cools and solidifies so the solidified bismuth does not expand and break the vanes.
Abstract translation: 一种具有用于冷却涡轮内的定子叶片的闭环液态金属冷却流体系统的燃气涡轮发动机，其中定子叶片由不会与液态金属冷却流体反应的金属材料制成。 定子叶片可以由诸如黑色金属合金，镍合金或钴（Co）合金的典型金属材料制成，并且可以将由钼或钽制成的插入件或衬垫放置在内部以保护外部叶片材料不与 液态金属如铋，铅（Pb），铟或其合金混合物。 在液体冷却剂为铋的情况下，液体铋在流体冷却并凝固之前必须从冷却系统中清除，因此凝固的铋不膨胀并破坏叶片。
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公开(公告)号：US08444389B1
公开(公告)日：2013-05-21
申请号：US12749580
申请日：2010-03-30
Applicant: Russell B Jones , John A Fedock
Inventor： Russell B Jones , John A Fedock
IPC: F01D5/14
CPC classification number: F01D5/14
Abstract: A multiple piece turbine rotor blade with a shell having an airfoil shape and secured between a spar and a platform with the spar including a tip end piece. a snap ring fits around the spar and abuts against the spar tip end piece on a top side and abuts against a shell on the bottom side so that the centrifugal loads from the shell is passed through the snap ring and into the spar and not through a tip cap dovetail slot and projection structure.
Abstract translation: 具有壳体的多片式涡轮转子叶片，其具有翼型并且固定在翼梁和平台之间，翼梁包括尖端部件。 卡环围绕翼梁并且抵靠在顶侧上的翼梁末端部件上并抵靠底侧的壳体，使得来自壳体的离心载荷通过卡环并进入翼梁，而不是通过 顶盖燕尾槽和投影结构。
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