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：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：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：US20160313212A1

公开(公告)日：2016-10-27

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 ,  F01D25/28 ,  F01D21/00 ,  G01M9/04 ,  G01M17/007

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.

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：US20160195018A1

公开(公告)日：2016-07-07

申请号：US14512070

申请日：2014-10-10

Applicant: Joseph D. Brostmeyer

Inventor： Joseph D. Brostmeyer

IPC: F02C7/18

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.

Abstract translation: 具有转子和定子的燃气涡轮发动机的涡轮机形成轮辋腔，其中所述转子包括具有通向所述轮辋腔的冷却空气通道的涡轮机转子叶片，以及可旋转地连接到所述转子的离心式叶轮，其中所述离心机 叶轮将加压的冷却空气排放到轮辋腔中，以改善轮辋腔密封并将加压的冷却空气供应到转子叶片冷却空气通道。

公开(公告)号：US20110296870A1

公开(公告)日：2011-12-08

申请号：US12778514

申请日：2010-05-12

Applicant: Joseph D. Brostmeyer

Inventor： Joseph D. Brostmeyer

IPC: F25J3/00

CPC classification number: B01D53/002 ,  B01D2257/302 ,  B01D2257/504 ,  B01D2257/80 ,  B01D2258/0283 ,  F23J15/06 ,  F23J15/08 ,  F23J2215/50 ,  F23J2219/70 ,  F23J2900/15061 ,  Y02E20/326 ,  Y02E20/363

Abstract: An apparatus and a process for separating carbon dioxide from a flue gas of a coal burning power plant. The process includes compressing the flue gas to increase the pressure and temperature, and then passing the flue gas through a cryogenic heat exchanger that decreases the temperature even more prior to passing the cooled carbon dioxide through a turbine that decreases the temperature more and forms liquid and solid forms carbon dioxide. A carbon dioxide separator then separates the carbon dioxide from the flue gas, leaving both liquid and solids forms. A screw compressor compresses the solid carbon dioxide to produce only liquid carbon dioxide at a pressure suitable for sequestration. The liquid carbon dioxide is passed through the heat exchanger to cool the flue gas and to separate out any sulfur dioxide and water from the flue gas and to vaporize the liquid carbon dioxide prior to sequestration of the vapor carbon dioxide.

Abstract translation: 一种用于从燃煤发电厂的烟道气中分离二氧化碳的装置和方法。 该方法包括压缩烟气以增加压力和温度，然后使烟道气通过低温热交换器，该低温热交换器在通过冷却的二氧化碳通过涡轮机之前更多地降低温度，所述涡轮机降低温度并形成液体和 固体形式二氧化碳。 二氧化碳分离器然后将二氧化碳与烟道气分离，形成液体和固体。 螺杆式压缩机压缩固体二氧化碳，以仅产生适于封存的压力的液体二氧化碳。 液态二氧化碳通过热交换器以冷却烟气并从烟道气中分离出任何二氧化硫和水，并在蒸发二氧化碳进行封存之前蒸发液态二氧化碳。

公开(公告)号：US20170298826A1

公开(公告)日：2017-10-19

申请号：US15131426

申请日：2016-04-18

Applicant: John E. Ryznic ,  Russell B. Jones ,  Joseph D. Brostmeyer ,  Justin T. Cejka

Inventor： John E. Ryznic ,  Russell B. Jones ,  Joseph D. Brostmeyer ,  Justin T. Cejka

IPC: F02C7/18 ,  F01P1/06 ,  F01D5/18 ,  F01D15/10 ,  H02K7/18 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D15/10 ,  F01P1/06 ,  F02C3/04 ,  F02C6/02 ,  F05D2230/80 ,  H02K7/1823 ,  Y02E20/16

Abstract: 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.

公开(公告)号：US20170241336A1

公开(公告)日：2017-08-24

申请号：US15157269

申请日：2016-05-17

Applicant: Russell B. Jones ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  John E. Ryznic

Inventor： Russell B. Jones ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  John E. Ryznic

IPC: F02C3/13 ,  F01D17/14 ,  F02C9/22 ,  F01D15/10 ,  F02C7/18 ,  F02C9/18

CPC classification number: F02C3/13 ,  F01D15/10 ,  F01D17/14 ,  F02C3/00 ,  F02C6/00 ,  F02C7/18 ,  F02C9/18 ,  F02C9/22 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2230/80 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2260/211

Abstract: A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.