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

IPC: F01D15/10 ,  F02C3/10 ,  F01D1/04 ,  F02C3/04 ,  F02C9/22

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.

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

IPC: F02C1/00 ,  F02C7/16 ,  F01D5/18 ,  F01D25/12 ,  F01D9/06

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。

公开(公告)号：US09410869B2

公开(公告)日：2016-08-09

申请号：US14934219

申请日：2015-11-06

Applicant: Joseph D Brostmeyer ,  Robert L Memmen

Inventor： Joseph D Brostmeyer ,  Robert L Memmen

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

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 combustor or a compressor of a gas turbine engine, 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 an air turbine to drive a compressor to produce high pressure and temperature compressed air, and where the compressed air can be discharged into a combustor and burned with a fuel for testing of the combustor under simulated conditions of a real gas turbine engine.

公开(公告)号：US07893556B1

公开(公告)日：2011-02-22

申请号：US12780967

申请日：2010-05-17

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 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的窄的主要支撑结构，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，垂直轴线涡轮机叶片从主体 支撑结构并在风中一起旋转，并且非旋转轴通过连接在主支撑结构和非旋转轴之间的垂直轴直接驱动发生器延伸通过主支撑结构，以在主支撑结构旋转时产生电力。 连接到非旋转轴的锚线防止浮动风力涡轮机在水体中漂移。

公开(公告)号：US08640437B1

公开(公告)日：2014-02-04

申请号：US13033633

申请日：2011-02-24

Applicant: Joseph D Brostmeyer

Inventor： Joseph D Brostmeyer

IPC: F02C6/18 ,  F01K23/10 ,  F02C7/36

CPC classification number: F02C6/18 ,  F01K23/10 ,  F02C1/05 ,  Y02E20/14 ,  Y02E20/16

Abstract: A mini combined cycle power plant with a mini gas turbine engine that operates at around 20,000 to 30,000 rpm and is connected to an electric generator through a speed reduction gear box, a low pressure steam turbine connected directly to the gas turbine engine, a high pressure steam turbine connected to the low pressure steam turbine through a smaller gear box so that the high pressure steam turbine can operate at around 70,000 to 100,000 rpm, and a heat recovery steam generator to use the turbine exhaust to produce high pressure steam for the two steam turbines. Leftover heat from the HRSG is used to heat homes or buildings in the local area to the power plant to improve the overall efficiency of the plant.

Abstract translation: 一种具有微型燃气涡轮发动机的微型联合循环发电机，其操作在20,000至30,000rpm左右，并通过减速齿轮箱，直接连接到燃气涡轮发动机的低压蒸汽轮机连接到发电机，高压 蒸汽轮机通过较小的齿轮箱连接到低压汽轮机，使得高压蒸汽轮机能够以大约70,000至100,000rpm的速度运行;以及热回收蒸汽发生器，以使用涡轮机排气来产生用于两个蒸汽的高压蒸汽 涡轮机。 来自HRSG的剩余热量用于将当地的家庭或建筑物加热到发电厂，以提高工厂的整体效率。

公开(公告)号：US07506555B2

公开(公告)日：2009-03-24

申请号：US11642256

申请日：2006-12-20

Applicant: Joseph D Brostmeyer ,  Jack W Wilson, Jr. ,  Todd A Ebert

Inventor： Joseph D Brostmeyer ,  Jack W Wilson, Jr. ,  Todd A Ebert

IPC: G01N17/00

CPC classification number: G01N25/00 ,  G01M15/14 ,  G01M99/002 ,  G01N3/18 ,  G01N17/002 ,  G01N2203/0042 ,  G01N2203/0057 ,  G01N2203/0226 ,  G01N2203/0232

Abstract: A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically sealed system that simulates conditions in hot sections or gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.

Abstract translation: 提供测试设备用于在高温，高压和机械负载下测试材料。 该设施提供了一个物理密封的系统，可模拟热段或燃气轮机的条件。 测试物品涂覆有测试材料并暴露于测试部分壳体中的热燃烧流。 制品可以是在流动的任何方向上定向的管道或管道构件。 流体的第二个较冷的流动通过测试物品，以在测试物品和测试材料中产生尖锐的温度梯度。 液体冷却的套筒围绕测试物品设置以产生在测试物品上燃烧的环形通道。 第二冷却器流的下游端连接到燃烧室的主热流的上游端。

公开(公告)号：US09810151B2

公开(公告)日：2017-11-07

申请号：US14512070

申请日：2014-10-10

Applicant: Joseph D Brostmeyer

Inventor： Joseph D Brostmeyer

IPC: F02C7/18 ,  F01D5/08

CPC classification number: F02C7/18 ,  F01D5/082 ,  F05D2220/3215 ,  F05D2260/20

Abstract: A turbine of a gas turbine engine with a rotor and a stator forming a rim cavity, where the rotor includes a turbine rotor blade with a cooling air channel opening into the rim cavity, and a centrifugal impeller rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel.

公开(公告)号：US09604756B1

公开(公告)日：2017-03-28

申请号：US15200057

申请日：2016-07-01

Applicant: Joseph D Brostmeyer ,  Robert L Memmen

Inventor： Joseph D Brostmeyer ,  Robert L Memmen

IPC: G01M15/14 ,  B65D19/16 ,  F02C6/16 ,  G01M17/007 ,  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 combustor of a gas turbine engine, 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 combustor to produce a decreased pressure such that a low atmospheric condition at the combustor exit is simulated.

公开(公告)号：US20160305261A1

公开(公告)日：2016-10-20

申请号：US15092292

申请日：2016-04-06

Applicant: John A Orosa ,  Joseph D Brostmeyer

Inventor： John A Orosa ,  Joseph D Brostmeyer

IPC: F01D9/02 ,  H02K7/18 ,  F01D15/10 ,  F01D5/18 ,  F02C3/04 ,  F02C9/18

CPC classification number: H02K7/1823 ,  F01D15/10 ,  F02C3/10 ,  F02C6/00 ,  F02C6/18 ,  F02C7/08 ,  F05D2220/72 ,  Y02E20/16

Abstract: 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.

Abstract translation: 用于电力生产的工业燃气涡轮发动机包括高压阀芯和低压阀芯，其中当完全关闭时，低压阀芯可以从全功率模式操作到零功率模式，其中低压阀芯在高压下运行 向高压阀芯的高压压缩机供应压缩空气的电力需求，并且其中涡轮机排气用于从热回收蒸汽发生器中产生的蒸汽驱动第二发电机。 高压阀芯包括具有内部压缩空气流动路径和外部压缩空气流动路径的高压压缩机，在该压缩空气流动路径中较高的压力向涡轮机翼片提供冷却，然后将其排出到发动机的燃烧器中。

公开(公告)号：US08770913B1

公开(公告)日：2014-07-08

申请号：US12817440

申请日：2010-06-17

Applicant: Antonio Negron ,  Joseph D Brostmeyer

Inventor： Antonio Negron ,  Joseph D Brostmeyer

IPC: F04D27/02

CPC classification number: F04D29/053 ,  F01D17/02 ,  F01D21/00 ,  F02C9/00 ,  F04D19/002 ,  F04D27/001 ,  F05D2260/80 ,  F05D2270/804

Abstract: An apparatus and a process for measuring rotor creep values for a monolithic rotor of an industrial gas turbine engine in order to determine when creep growth of the rotor has exceeded an allowable limit. One or more critical locations of the rotor are measured for real-time radius, and a CPU having rotor creep deflection model is used to compare the real-time data and determine if the rotor creep is within safe and allowable limits. If the creep is determined to exceed allowable values, then an alarm in initiated or engine shutdown occurs.

Abstract translation: 用于测量工业燃气涡轮发动机的单片转子的转子蠕变值的装置和方法，以便确定转子的蠕变生长是否已经超过允许极限。 测量转子的一个或多个关键位置用于实时半径，并且使用具有转子蠕变偏转模型的CPU来比较实时数据并确定转子蠕变是否在安全和允许的极限内。 如果蠕变确定超过允许值，则发生启动或发动机关闭时发生报警。