公开(公告)号：US08721265B1

公开(公告)日：2014-05-13

申请号：US13946003

申请日：2013-07-19

Applicant: Joseph D Brostmeyer ,  John E Ryznic

Inventor： Joseph D Brostmeyer ,  John E Ryznic

IPC: F01D5/14 ,  F03B11/00 ,  F03D11/00 ,  F04D29/38

CPC classification number: F04D29/584 ,  F01D5/187 ,  F02C6/08 ,  F02C7/18 ,  F02C7/224 ,  F04D19/02 ,  F04D29/324 ,  F04D29/542 ,  F05D2220/3219 ,  F05D2260/205 ,  Y02T50/676

Abstract: A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. A portion of the compressed air from the discharge of the compressor is bled off and passed through a heat exchanger to preheat a fuel and to cool the compressed air. The cooled compressed air is then passed through the last stage airfoil of the compressor to provide cooling. The cooling air is then reintroduced back into the compressor at an earlier stage or passed through an airfoil in the turbine to provide cooling.

Abstract translation: 具有多级翼型件以产生高压口径的高压缩比压缩机，其中通过使冷却空气通过翼型件而不排放膜冷却空气来冷却最后级翼型件。 来自压缩机排出的压缩空气的一部分被排出并通过热交换器以预热燃料并冷却压缩空气。 冷却的压缩空气然后通过压缩机的最后一级翼型件以提供冷却。 然后冷却空气在较早的阶段被重新引入压缩机，或者通过涡轮机中的翼型以提供冷却。

公开(公告)号：US08505181B1

公开(公告)日：2013-08-13

申请号：US13478005

申请日：2012-05-22

Applicant: Joseph D Brostmeyer ,  Andrew R Narcus

Inventor： Joseph D Brostmeyer ,  Andrew R Narcus

IPC: B23Q17/00

CPC classification number: F01D5/005 ,  F01D5/141 ,  F01D21/003 ,  F05D2270/708 ,  F05D2270/71 ,  F05D2270/8041 ,  Y10T29/49758 ,  Y10T29/49764 ,  Y10T29/49771

Abstract: A process for redesigning a distressed component in which the distressed component is under thermal and structural loads, for improving the life of the component. The process includes obtaining the operating conditions of the machine in which the distressed component is used, finding the boundary conditions under which the distressed component operates, producing a 3-dimensional model of the distressed component with such detail that the distress levels are accurately represented on the model, subjecting the model to a series of technical analysis to predict a life for the component, reiterating the technical analysis until the levels of distress on the model accurately represent the distress that appears on the actual component, and then predicting a remaining life of the component based on the analysis, or redesigning the model and reanalyzing the model until a maximum life for the component has been found.

Abstract translation: 一种重新设计遇险部件的过程，其中受损部件处于热和结构负载下，以改善部件的使用寿命。 该过程包括获得其中使用受损部件的机器的操作条件，找到遇险部件在其下运行的边界条件，产生不良部件的3维模型，其中具有如下细节：遇险水平被准确地表示在 模型，对模型进行一系列技术分析以预测组件的生命，重申技术分析，直到模型的困扰程度准确地表示出现在实际组件上的痛苦，然后预测剩余寿命 基于分析的组件，或重新设计模型并重新分析模型，直到找到组件的最大寿命。

公开(公告)号：US08209839B1

公开(公告)日：2012-07-03

申请号：US12849218

申请日：2010-08-03

Applicant: Joseph D Brostmeyer ,  Andrew R Narcus

Inventor： Joseph D Brostmeyer ,  Andrew R Narcus

IPC: B23Q17/00

CPC classification number: F01D5/005 ,  F01D5/141 ,  F01D21/003 ,  F05D2270/708 ,  F05D2270/71 ,  F05D2270/8041 ,  Y10T29/49758 ,  Y10T29/49764 ,  Y10T29/49771

Abstract: A process for redesigning a distressed component, such as a turbine blade in a gas turbine engine, in which the distressed component is under thermal and structural loads, for improving the life of the component. The process includes obtaining the operating conditions of the machine in which the distressed component is used, finding the boundary conditions under which the distressed component operates, producing a 3-dimensional model of the distressed component with such detail that the distress levels are accurately represented on the model, subjecting the model to a series of technical analysis to predict a life for the component, reiterating the technical analysis until the levels of distress on the model accurately represent the distress that appears on the actual component, and then predicting a remaining life of the component based on the analysis, or redesigning the model and reanalyzing the model until a maximum life for the component has been found. When the maximum (or near maximum) life for a component has been found, the component is then manufactured with the new component having an increased life and possibly increased performance level.

Abstract translation: 用于重新设计诸如燃气涡轮发动机中的涡轮叶片的不良部件的过程，其中受损部件处于热和结构负载下，以改善部件的寿命。 该过程包括获得其中使用受损部件的机器的操作条件，找到遇险部件在其下运行的边界条件，产生不良部件的3维模型，其中具有如下细节：遇险水平被准确地表示在 模型，对模型进行一系列技术分析以预测组件的生命，重申技术分析，直到模型的困扰程度准确地表示出现在实际组件上的痛苦，然后预测剩余寿命 基于分析的组件，或重新设计模型并重新分析模型，直到找到组件的最大寿命。 当已经找到组件的最大（或接近最大）寿命时，然后使用具有增加的寿命和可能增加的性能水平的新组件来制造组件。

公开(公告)号：US09654161B2

公开(公告)日：2017-05-16

申请号：US15200102

申请日：2016-07-01

Applicant: Joseph D Brostmeyer ,  Robert L Memmen

Inventor： Joseph D Brostmeyer ,  Robert L Memmen

IPC: G01M15/14 ,  H04B1/16 ,  G01M17/007 ,  F02C6/16 ,  G01M9/02

CPC classification number: H04B1/1646 ,  B65D19/16 ,  F01D5/02 ,  F01D17/02 ,  F01D21/003 ,  F01D25/285 ,  F02C6/16 ,  F04D27/001 ,  F04D29/321 ,  F05B2220/302 ,  F05B2260/83 ,  F05D2220/323 ,  F05D2260/83 ,  F23R2900/00019 ,  G01M9/02 ,  G01M9/04 ,  G01M15/14 ,  G01M17/007 ,  Y02E60/15

Abstract: A process for testing a turbine of a gas turbine engine at high altitudes, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.

公开(公告)号：US09500564B2

公开(公告)日：2016-11-22

申请号：US15200125

申请日：2016-07-01

Applicant: Joseph D Brostmeyer ,  Robert L Memmen

Inventor： Joseph D Brostmeyer ,  Robert L Memmen

IPC: G01M15/14 ,  G01M9/04 ,  G01M17/007 ,  F01D21/00 ,  F01D25/28

CPC classification number: H04B1/1646 ,  B65D19/16 ,  F01D5/02 ,  F01D17/02 ,  F01D21/003 ,  F01D25/285 ,  F02C6/16 ,  F04D27/001 ,  F04D29/321 ,  F05B2220/302 ,  F05B2260/83 ,  F05D2220/323 ,  F05D2260/83 ,  F23R2900/00019 ,  G01M9/02 ,  G01M9/04 ,  G01M15/14 ,  G01M17/007 ,  Y02E60/15

Abstract: A process for testing a full-sized aircraft or full-sized gas turbine engine in a wind tunnel and includes the steps of securing a full-sized aircraft or engine in a wind tunnel for testing; filling an underground storage reservoir with compressed air; passing pre-treated compressed air from the underground storage reservoir through the wind tunnel for testing of the full-sized aircraft or engine; connecting an outlet of the wind tunnel to an ejector; and, passing compressed air from the underground storage reservoir through the ejector to decrease the exit pressure at the wind tunnel during testing of the full-sized aircraft or engine. The step of pre-treating compressed air from the underground storage reservoir includes preheating the compressed air; and, passing the higher temperature compressed air into the wind tunnel.

Abstract translation: 一种用于在风洞中测试全尺寸飞机或全尺寸燃气涡轮发动机的过程，包括将全尺寸飞机或发动机固定在风洞中以进行测试的步骤; 用压缩空气填充地下储存库; 将来自地下储存库的预处理压缩空气通过风洞，以测试全尺寸飞机或发动机; 将风洞的出口连接到喷射器; 并且在全尺寸飞行器或发动机测试期间，通过喷射器将压缩空气从地下储存容器通过，以降低风洞处的出口压力。 从地下储存容器预处理压缩空气的步骤包括预热压缩空气; 并将较高温度的压缩空气通入风洞。

公开(公告)号：US08789377B1

公开(公告)日：2014-07-29

申请号：US14056992

申请日：2013-10-18

Applicant: Joseph D Brostmeyer ,  John W Appleby, Jr.

Inventor： Joseph D Brostmeyer ,  John W Appleby, Jr.

IPC: F02C7/12 ,  F02C7/00

CPC classification number: F02C7/16 ,  F05D2300/1606 ,  F05D2300/1612

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 include a liquid metal cooling passage lined with Tantalum or Molybdenum and a liquid metal cooling fluid of Bismuth or Lead or Zinc or Tin or alloy mixtures of these metals.

Abstract translation: 一种具有用于冷却涡轮机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，其中定子叶片包括衬有钽或钼的液态金属冷却通道和铋或铅或锌的液态金属冷却流体， 锡或这些金属的合金混合物。

公开(公告)号：US08277193B1

公开(公告)日：2012-10-02

申请号：US12957488

申请日：2010-12-01

Applicant: Joseph D Brostmeyer ,  William L Plank

Inventor： Joseph D Brostmeyer ,  William L Plank

IPC: F01D25/14

CPC classification number: F01D5/147 ,  F05D2230/10 ,  F05D2230/14 ,  Y10T29/49341

Abstract: A thin wall turbine blade used in a gas turbine engine, in which the blade is cast in conventional grain from a super alloy using the lost wax process as a single piece, and then the blade walls are machined to remove enough material to leave a thin wall. The blade is cast with a wall thickness greater than the designed for thin wall in order that any core shifting during the casting process will be accounted for in the machining process. prior to machining, a scanning process is used to measure the actual wall thickness on all portions of the blade wall in order to determine how much material must be removed to leave the blade wall with the proper thinness.

Abstract translation: 用于燃气涡轮发动机中的薄壁涡轮机叶片，其中叶片以常规晶粒从超级合金铸造，使用失蜡法作为单件，然后将叶片壁加工以除去足够的材料以留下薄的 壁。 刀片的浇铸厚度大于为薄壁设计的壁厚，以便在铸造过程中的任何芯移动将在加工过程中得到考虑。 在加工之前，使用扫描过程来测量叶片壁的所有部分上的实际壁厚，以便确定必须移除多少材料以使叶片壁具有合适的薄度。

公开(公告)号：US08205456B1

公开(公告)日：2012-06-26

申请号：US12841271

申请日：2010-07-22

Applicant: Joseph D Brostmeyer

Inventor： Joseph D Brostmeyer

IPC: F02C6/00

CPC classification number: F02C6/18 ,  F01K23/10 ,  F01K23/103 ,  F02C1/04 ,  F02C7/08 ,  F05D2220/31 ,  F05D2240/40 ,  Y02E20/14 ,  Y02E20/16 ,  Y02E50/12

Abstract: A power plant for burning a fuel in a low pressure combustion chamber to produce electrical power. A first compressor supplies compressed air through a first heat exchanger to add heat to the compressed air. The heated compressed air is passed through a first turbine to drive a first electric generator. The first turbine outlet is passed through a second heat exchanger in series with the first heat exchanger to further heat the compressed air. The compressed air is then passed through a second turbine to drive a second electric generator and produce electric power. The outlet from the second turbine is passed through a first combustor to produce the hot gas flow through the second heat exchanger. The outlet from the second heat exchanger is passed through a second combustor before passing through the first heat exchanger. The outlet from the first heat exchanger is passed through a heat recovery steam generator to generate steam to drive another turbine and another generator. An additional compressor and intercooler can be used to supply the compressed air to the first heat exchanger. With this system, one or more fuels can be burned under low pressure and without passing the contaminants from combustion through the turbines.

Abstract translation: 一种用于在低压燃烧室中燃烧燃料以产生电力的发电厂。 第一压缩机通过第一热交换器供应压缩空气以向压缩空气加热。 加热的压缩空气通过第一涡轮以驱动第一发电机。 第一涡轮机出口通过与第一热交换器串联的第二热交换器，以进一步加热压缩空气。 压缩空气然后通过第二涡轮以驱动第二发电机并产生电力。 来自第二涡轮机的出口通过第一燃烧器以产生通过第二热交换器的热气流。 来自第二热交换器的出口在通过第一热交换器之前通过第二燃烧器。 来自第一热交换器的出口通过热回收蒸汽发生器以产生蒸汽以驱动另一涡轮机和另一发电机。 可以使用附加的压缩机和中间冷却器来将压缩空气供应到第一热交换器。 利用该系统，可以在低压下燃烧一种或多种燃料，并且不会使污染物通过涡轮机燃烧。

公开(公告)号：US07937946B1

公开(公告)日：2011-05-10

申请号：US11642257

申请日：2006-12-20

Applicant: Mark M Harris ,  Joseph D Brostmeyer

Inventor： Mark M Harris ,  Joseph D Brostmeyer

IPC: F02C7/00

CPC classification number: F02C7/224 ,  F01D25/18 ,  F02C7/06 ,  F02C7/22 ,  F05D2250/82

Abstract: A small gas turbine engine with a bearing cooling and lubricating passage arrangement for a high speed rotor shaft. The engine includes a bypass fan and a compressor. The rotor shaft includes a central passage extending through the entire shaft, and where the rotor shaft is supported by a forward bearing and a rearward bearing. Cooling air for the bearings is diverted from the bypass air and is channeled through the bearings. Fuel is added to the cooling air at a location upstream of the bearing to provide lubrication. The cooling air and lubricating fuel passes through the bearings and into the rotating central shaft, and is then forced to flow toward a radial passage located adjacent to the combustor. The fuel is collected on the central shaft surface and forced out the radial passage and into the combustor. The cooling air continuous out from the central shaft to be mixed with the engine exhaust.

Abstract translation: 一种具有用于高速转子轴的轴承冷却和润滑通道装置的小型燃气涡轮发动机。 发动机包括旁通风扇和压缩机。 转子轴包括延伸穿过整个轴的中心通道，转子轴由前轴承和后轴承支撑。 轴承的冷却空气从旁路空气转移并通过轴承。 在轴承上游的位置处将燃料添加到冷却空气中以提供润滑。 冷却空气和润滑油通过轴承并进入旋转中心轴，然后被迫流向邻近燃烧器的径向通道。 燃料被收集在中心轴表面上并被迫离开径向通道并进入燃烧器。 冷却空气从中心轴连续地与发动机排气混合。

公开(公告)号：US07750492B1

公开(公告)日：2010-07-06

申请号：US12613305

申请日：2009-11-05

Applicant: John E Ryznic ,  Joseph D Brostmeyer ,  Jack W Wilson, Jr.

Inventor： John E Ryznic ,  Joseph D Brostmeyer ,  Jack W Wilson, Jr.

IPC: F03D3/04

CPC classification number: F03D3/005 ,  F03D13/25 ,  F05B2220/7066 ,  F05B2220/7068 ,  F05B2240/212 ,  F05B2240/301 ,  F05B2240/61 ,  F05B2240/93 ,  F05B2240/95 ,  F05B2260/85 ,  F05B2260/90 ,  Y02E10/727 ,  Y02E10/74

Abstract: A bearingless floating wind turbine has a tall and narrow main support structure with a center of buoyancy located well above the center of gravity to provide stability to the wind turbine while supported for rotation in a body of water, a vertical axis turbine blade extends from the main support structure and rotates together under a wind, and a non-rotating shaft extends through the main support structure with a vertical axis direct drive generator connected between the main support structure and the non-rotating shaft to produce electricity when the main support structure rotates. an anchor line connected to the non-rotating shaft prevents the floating wind turbine from drifting in a body of water.

Abstract translation: 无轴承浮动风力涡轮机具有高而窄的主支撑结构，其浮力中心位于重心之上，以便在风力涡轮机同时被支撑以在水体中旋转时提供稳定性，垂直轴涡轮机叶片从 主支撑结构并在风中一起旋转，并且非旋转轴通过主支撑结构延伸，其中垂直轴直接驱动发电机连接在主支撑结构和非旋转轴之间，以在主支撑结构旋转时产生电力 。 连接到非旋转轴的锚定线防止浮动风力涡轮机在水体中漂移。