公开(公告)号：US20170342854A1

公开(公告)日：2017-11-30

申请号：US15137248

申请日：2016-04-25

Applicant: Barry J. Brown ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

Inventor： Barry J. Brown ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

IPC: F01D17/16 ,  F02C3/04 ,  F01D15/10 ,  F04D29/40 ,  H02P9/04 ,  F01K23/10 ,  F02C6/18

CPC classification number: F01D17/16 ,  F01D15/10 ,  F01D17/162 ,  F01K23/106 ,  F02C3/04 ,  F02C3/13 ,  F02C6/04 ,  F02C6/18 ,  F02C9/20 ,  F02C9/22 ,  F04D29/403 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2240/128 ,  F05D2270/023 ,  F05D2270/053 ,  F05D2270/061 ,  H02P9/04 ,  Y02E20/16

Abstract: A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.

公开(公告)号：US08250851B1

公开(公告)日：2012-08-28

申请号：US13050828

申请日：2011-03-17

Applicant: Joseph D. Brostmeyer

Inventor： Joseph D. Brostmeyer

IPC: F02C3/00

CPC classification number: F01D9/023 ,  F05B2260/3011 ,  F05D2240/12 ,  F05D2300/607

Abstract: A transition duct used in a gas turbine engine to direct the hot gas flow from the combustor into the turbine section of the gas turbine engine. The transition duct includes a plurality of guide vane integral with the duct. The transition duct includes a circular shaped inlet end for connection to a can combustor and a rectangular and arched shaped outlet end for connection to a first stage turbine section. the guide vanes extend within the flow path between inner and outer projections each having a curved opening in the shape of the airfoil each airfoil includes inner and outer airfoil ends with retainer slots formed between the airfoil ends and the duct projections that form shear pin retainer slots. Shear pin retainers are secured within the slots to secure the guide vanes to the duct in a thermally uncoupled manner to reduce thermal stresses. The guide vanes can be made from a single crystal material for higher gas flow temperatures.

Abstract translation: 一种用于燃气涡轮发动机的过渡管道，用于将来自燃烧器的热气流引导到燃气涡轮发动机的涡轮部分。 过渡管道包括与导管一体的多个导向叶片。 过渡管道包括用于连接到罐式燃烧器的圆形入口端和用于连接到第一级涡轮机部分的矩形和拱形出口端。 导向叶片在内部和外部突出部之间的流动路径内延伸，每个翼部具有翼型形状的弯曲开口，每个翼型件包括形成有翼型端部和管道突起之间的保持槽的内部和外部翼型端部，形成剪切销保持器狭槽 。 剪切销保持器固定在槽内以将导叶以热脱开的方式固定到管道上以减少热应力。 引导叶片可以由单晶材料制成，用于更高的气体流动温度。

公开(公告)号：US20180010476A1

公开(公告)日：2018-01-11

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 ,  F01D1/04 ,  F02C3/10 ,  F02C3/04 ,  F02C9/22

CPC classification number: F01D15/10 ,  F01D1/04 ,  F02C3/04 ,  F02C3/10 ,  F02C9/20 ,  F02C9/22 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/3213 ,  F05D2220/3215 ,  F05D2220/76 ,  F05D2230/80

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：US09200983B2

公开(公告)日：2015-12-01

申请号：US14008308

申请日：2012-03-15

Applicant: Joseph D. Brostmeyer

Inventor： Joseph D. Brostmeyer

IPC: G01M15/14

CPC classification number: G01M15/14

Abstract: A system and a process for testing a gas turbine engine or component thereof, especially for a large aero gas turbine engine, and for a process for testing a large industrial gas turbine engine that requires large flow capacity and pressure ratios. The system and process may include the use of a large compressed air storage reservoir to provide compressed air to the testing system. Further, the system and process may also include the use of a pre-heating system, which may include a heater and a heat exchange device, to warm the compressed air from the compressed air storage reservoir to a temperature suitable to simulate normal operating conditions of the gas turbine engine or component thereof.

Abstract translation: 一种用于测试燃气涡轮发动机或其部件，特别是用于大型航空燃气涡轮发动机的系统和过程，以及用于测试需要大流量和压力比的大型工业燃气涡轮发动机的方法。 系统和过程可以包括使用大的压缩空气存储容器来向测试系统提供压缩空气。 此外，系统和过程还可以包括使用预热系统，其可以包括加热器和热交换装置，以将压缩空气从压缩空气存储容器加热至适于模拟正常操作条件的温度 燃气涡轮发动机或其部件。

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：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.

公开(公告)号：US20170022905A1

公开(公告)日：2017-01-26

申请号：US15137280

申请日：2016-04-25

Applicant: John A. Orosa ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

Inventor： John A. Orosa ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

IPC: F02C9/18 ,  F02C7/18 ,  F02C3/04

CPC classification number: F02C9/18 ,  F02C3/04 ,  F02C6/08 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/205 ,  F05D2260/213

Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.

Abstract translation: 一种具有高阀芯和低阀芯的工业燃气涡轮发动机，其中低压压缩空气被供应到高压压缩机，并且其中一部分低压压缩空气被排出以用作冷却空气中的热部件 发动机的高压汽轮机。 环形泄放通道位于LPC扩散器中。 排放通道泄漏约15％的核心流量，并将排出的空气通入冷却流道，然后流入涡轮机热部分的冷却回路。