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1. 发明申请

WO2021260531A1 MULTI-SPOOL GEARED TURBOFAN ARRANGEMENT WITH INTEGRATED STARTER/GENERATOR 审中-公开
公开(公告)号：WO2021260531A1
公开(公告)日：2021-12-30
申请号：PCT/IB2021/055464
申请日：2021-06-21
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph D. , RESS JR., Robert A. , SLOSS, Tyler W. , BROWN, Barry J.
IPC分类号： F02C3/107 , F02K3/06 , F02C7/06 , F01D15/10 , F01D15/12 , F01D25/16 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2240/50
摘要： A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. The low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft. The speed reduction gear box is positioned between and mechanically couples the high speed shaft and the low speed shaft, which allows the fan and the integrated starter/generator on the low speed shaft to operate at a lower speed than the high speed shaft.

2. 发明申请

WO2018203941A3 TURBOCHARGED GAS TURBINE ENGINE WITH ELECTRIC POWER GENERATION FOR SMALL AIRCRAFT ELECTRIC PROPULSION 审中-公开
公开(公告)号：WO2018203941A3
公开(公告)日：2018-11-08
申请号：PCT/US2018/015716
申请日：2018-01-29
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： JONES, Russell B. , RESS, JR., Robert A.
IPC分类号： F02C3/107
摘要： A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main fan and a high spool that drives a high speed electric generator. The low pressure compressor supplies low pressure air to an inlet of the high pressure compressor. A row of stator vanes in the high pressure turbine is cooled using cooling air bled off from the low pressure compressor outlet that is passed through an intercooler and a boost compressor, where the spent vane cooling air is discharged into the combustor. The low pressure turbine and the two compressors each include a variable inlet guide vane to control the power level of the engine. Bypass flow from the main fan is used to cool hot parts of the engine.

3. 发明申请

WO2018132123A1 TURBINE STATOR VANE WITH MULTIPLE OUTER DIAMETER PRESSURE FEEDS 审中-公开
公开(公告)号：WO2018132123A1
公开(公告)日：2018-07-19
申请号：PCT/US2017/035359
申请日：2017-06-01
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： CUPINI, Michelle, I. , MURRAY, Stephen, E.
IPC分类号： F01D9/06 , F01D5/18 , F01D9/04
摘要： The invention is related to a stator vane assembly for a gas turbine engine in which both higher pressure cooling air and lower pressure cooling air are both supplied to the stator vane assembly to cool both an airfoil (20) and inner and outer diameter endwall cavities (17,18) of the stator vane assembly, in which the spent higher pressure cooling air is then discharged into a combustor of the gas turbine engine. The higher pressure cooling air flows through a closed loop cooling circuit formed within the stator vane assembly while the lower pressure cooling air is discharged through exit holes (21) into the hot gas stream of the turbine. The high pressure closed loop cooling circuit comprises supply (13) and exit (15), which are interconnected via tubes (25) and an internal airfoil cooling circuit (14). Thus, thermodynamic efficienccy is increased by reducing leakages and mixing losses.

4. 发明申请

WO2017189566A3 TWIN SPOOL INDUSTRIAL GAS TURBINE ENGINE WITH VARIABLE INLET GUIDE VANES 审中-公开
标题翻译： TWIN SPOOL工业燃气涡轮发动机，带有可变入口导向槽
公开(公告)号：WO2017189566A3
公开(公告)日：2017-11-02
申请号：PCT/US2017/029401
申请日：2017-04-25
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： MURRAY, Stephen, E. , BROSTMEYER, Joseph, D. , JONES, Russell B. , BROWN, Barry, J. , CEJKA, Justin, T.
IPC分类号： F01D15/10 , F01D17/16 , F02C3/04 , F04D27/02 , F02C6/12 , F02C9/20 , F02C9/54
摘要： A large frame heavy duty industrial gas turbine engine that produces twice the power as conventional single spool industrial engines and operates at full power during a hot day. The engine includes a high spool directly driving an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine (LPT) driving a low pressure compressor (LPC) from the exhaust gas from the high pressure turbine.. The low spool can operate at a higher speed than at the normal temperature conditions to produce high mass flow. A turbine with a variable IGV assembly in which vane airfoils extend between inner and outer buttons, an airfoil center of rotation being located aft of an airfoil aerodynamic center of pressure. The airfoil trailing edge (TE) extends into both buttons to eliminate gap between the airfoil TE and a static part of the turbine.
摘要翻译：大型机架重型工业燃气涡轮发动机的功率是传统单轴工业发动机的两倍，并在炎热的一天中以全功率运行。发动机包括直接以电力网的同步速度驱动发电机的高阀芯，具有低压涡轮（LPT）的低阀芯，低压涡轮（LPT）驱动来自高压涡轮的排气的低压压缩机（LPC）。。低速阀芯可以以比常温条件更高的速度运转，以产生高质量流量。具有可变IGV组件的涡轮机，其中叶片翼面在内部和外部按钮之间延伸，翼型旋转中心位于翼型空气动力学压力中心的后面。翼型后缘（TE）延伸到两个按钮中以消除翼型TE与涡轮静态部分之间的间隙。

5. 发明申请

WO2017151146A1 AIR COOLED TURBINE STATOR VANES 审中-公开
标题翻译：空气冷却式汽轮机静子
公开(公告)号：WO2017151146A1
公开(公告)日：2017-09-08
申请号：PCT/US2016/020945
申请日：2016-03-04
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： MEMMEN, Robert, L.
IPC分类号： F01D9/06 , F01D5/18 , F01D11/00 , B22F5/04
摘要： An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which flexible seals (14) are located, and where the backside surface of the airfoil and the insert include chordwise (19, 22, 24, 26) and sideways bumper surfaces (18, 21, 23, 25) each having a gap to allow for relative movement of the insert within the cavity from thermal gradients while maintaining a seal between the airfoil and the impingement cooling insert. Each flexible seal has an X-shaped cross-section having four points that each makes contact with a surface of the respective seal slot so that a high relative movement of the impingement cooling insert within the cavity can occur while still maintaining a tight seal. The impingement cooling insert includes a number of crossover tubes (27) connecting return air holes on a pressure side to impingement holes on a suction side of the impingement cooling insert.
摘要翻译：具有固定在空腔内的冲击式冷却插入件（12,13）的空气冷却涡轮定子叶片，其中在翼型的后侧表面和冲击冷却之间形成前和后密封槽其中柔性密封件（14）位于其中的插入件，并且其中翼型件和插入件的后侧表面包括弦向（19,22,24,26）和侧向缓冲器表面（18,21,23,25），每个缓冲器表面具有间隙以允许插入件在空腔内从热梯度相对运动，同时保持翼型和冲击冷却插入件之间的密封。每个柔性密封件具有X形横截面，该X形横截面具有四个点，每个点与相应密封槽的表面接触，使得冲击冷却插入件在空腔内的高度相对运动可以发生，同时仍保持紧密密封。冲击冷却插入件包括多个交叉管（27），其将压力侧上的返回空气孔连接到冲击冷却插入件的吸入侧上的冲击孔。

6. 发明申请

WO2016127187A2 APPARATUS AND PROCESS OF RETROFITTING A COMBINED CYCLE POWER PLANT 审中-公开
标题翻译：装置和改造组合循环发电厂的过程
公开(公告)号：WO2016127187A2
公开(公告)日：2016-08-11
申请号：PCT/US2016/023764
申请日：2016-03-23
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph D. , JONES, Russell B. , CEJKA, Justin T. , OROSA, John A. , RYZNIC, John E.
IPC分类号： F01D25/08
CPC分类号： F02C7/185 , F01D9/041 , F01D25/08 , F01D25/12 , F01K23/10 , F02C3/06 , F02C3/13 , F02C6/08 , F02C6/18 , F05D2220/32 , F05D2220/76 , F05D2230/80 , F05D2260/211 , Y02E20/16 , Y02T50/675
摘要： A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.
摘要翻译：一种使用两台60赫兹大型框架重负荷工业燃气涡轮发动机来驱动发电机并发电的电厂的改造工艺，两台工业发动机中的每一台都可以生产高达350兆瓦的电力的输出功率。该工艺用两台350 MW的工业发动机替代了一台双轴工业燃气涡轮发动机，该发动机至少可以产生700 MW的输出功率。因此，两个现有技术的工业发动机可以用一个工业发动机来代替，该工业发动机可以产生相当于两个现有技术的工业发动机的功率。

7. 发明申请

WO2019245563A1 PROCESS FOR REFINING FEATURES IN AN ADDITIVE MANUFACTURED PART AND MANUFACTURED PART WITH REFINED FEATURES 审中-公开
公开(公告)号：WO2019245563A1
公开(公告)日：2019-12-26
申请号：PCT/US2018/038747
申请日：2018-06-21
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： JONES, Russell, B.
IPC分类号： B22F3/105 , B22F5/10 , B23P15/04 , F01D5/00 , B33Y80/00 , B33Y10/00
摘要： 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.

8. 发明申请

WO2018222192A1 HIGH PRESSURE RATIO TWIN SPOOL INDUSTRIAL GAS TURBINE ENGINE WITH DUAL FLOW HIGH SPOOL COMPRESSOR 审中-公开
公开(公告)号：WO2018222192A1
公开(公告)日：2018-12-06
申请号：PCT/US2017/035348
申请日：2017-06-01
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： OROSA, John, A. , BROSTMEYER, Joseph, D.
IPC分类号： F02C3/06 , F01D5/02 , F01D5/14 , F01D25/12 , F02C7/18 , F02C6/08
CPC分类号： F02C3/064 , F01D5/022 , F01D25/12 , F02C6/08 , F02C7/18 , F05D2220/76
摘要： An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, where the low pressure spool is operated at high electrical demand to supply compressed air to the high pressure compressor of the high pressure spool, and where turbine exhaust is used to drive a second electric generator from steam produced in a heat recovery steam generator. The high pressure spool includes a high pressure compressor with a inner compressed air flow path and an outer compressed air flow path in which a higher pressure supplies cooling to a turbine airfoil that is then discharged into a combustor of the engine.

9. 发明申请

WO2018022015A1 TURBOCHARGER WITH OIL-FREE HYDROSTATIC BEARING 审中-公开
标题翻译：无油静压轴承的涡轮增压器
公开(公告)号：WO2018022015A1
公开(公告)日：2018-02-01
申请号：PCT/US2016/044056
申请日：2016-07-26
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： PINERA, Alex , MILLER, Timothy J.
IPC分类号： F04D29/057 , F16C32/06 , F01D25/22
摘要： A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings (15, 16) in both a radial and an axial direction by a compressed air supplied from a compressor (11) of the turbocharger and boosted in pressure by a separate boost compressor (17) to a high enough pressure to support the rotor of the turbocharger. The turbocharger hydrostatic bearings (15, 16) are damped using wire mesh or dispersed friction dampers (33, 41).
摘要翻译：一种用于内燃机的涡轮增压器，所述涡轮增压器由涡轮增压器的压缩机（11）供应的压缩空气在径向和轴向两个方向上由静压轴承（15,16）支撑并通过单独的增压压缩机（17）增压到足够高的压力以支撑涡轮增压器的转子。涡轮增压器静压轴承（15,16）使用丝网或分散式摩擦阻尼器（33,41）进行减振。

10. 发明申请

WO2017189566A2 TWIN SPOOL INDUSTRIAL GAS TURBINE ENGINE WITH VARIABLE INLET GUIDE VANES 审中-公开
公开(公告)号：WO2017189566A2
公开(公告)日：2017-11-02
申请号：PCT/US2017/029401
申请日：2017-04-25
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： MURRAY, Stephen, E. , BROSTMEYER, Joseph, D. , JONES, Russell B. , BROWN, Barry, J. , CEJKA, Justin, T.
IPC分类号： F01D15/10 , F01D17/16 , F02C3/04 , F04D27/02 , F02C6/12 , F02C9/20 , F02C9/54
CPC分类号： F02C3/04 , F01D15/10 , F01D17/16 , F02C6/12 , F02C9/20 , F02C9/54 , F04D27/0246 , F05D2220/40 , F05D2220/76 , F05D2260/70 , Y02E20/16
摘要： A large frame heavy duty industrial gas turbine engine that produces twice the power as conventional single spool industrial engines and operates at full power during a hot day. The engine includes a high spool directly driving an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine (LPT) driving a low pressure compressor (LPC) from the exhaust gas from the high pressure turbine.. The low spool can operate at a higher speed than at the normal temperature conditions to produce high mass flow. A turbine with a variable IGV assembly in which vane airfoils extend between inner and outer buttons, an airfoil center of rotation being located aft of an airfoil aerodynamic center of pressure. The airfoil trailing edge (TE) extends into both buttons to eliminate gap between the airfoil TE and a static part of the turbine.

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