公开(公告)号：US20070220900A1

公开(公告)日：2007-09-27

申请号：US11389711

申请日：2006-03-27

Applicant: Michael Shockling ,  Karl Sheldon

Inventor： Michael Shockling ,  Karl Sheldon

IPC: F02C6/00

CPC classification number: F02C3/22 ,  F02C6/04 ,  F02C6/08

Abstract: A non-aircraft-propelling auxiliary gas turbine engine assembly includes an auxiliary gas turbine engine and a mixing damper. The auxiliary engine and the mixing damper are installable in an aircraft having at least one aircraft-propelling main gas turbine engine. The auxiliary engine includes a compressor having a compressor inlet. The mixing damper has first and second inlets and has an outlet. The outlet is fluidly connectable to the compressor inlet. The first and second inlets are adapted to receive first and second gas streams which have been compressed by at least one main engine. An aircraft component includes a mixing damper. A controller includes a program which instructs the controller to increase/decrease a first gas stream in response to increasing/decreasing electrical demands on an electric generator operatively connected to an auxiliary gas turbine engine of an aircraft.

Abstract translation: 非飞机推进辅助燃气涡轮发动机组件包括辅助燃气涡轮发动机和混合阻尼器。 辅助发动机和混合阻尼器可安装在具有至少一个飞机推进主燃气涡轮发动机的飞行器中。 辅助发动机包括具有压缩机入口的压缩机。 混合阻尼器具有第一和第二入口并具有出口。 出口可流体地连接到压缩机入口。 第一和第二入口适于接受已被至少一个主发动机压缩的第一和第二气流。 飞机部件包括混合阻尼器。 控制器包括指示控制器响应于对与飞机的辅助燃气涡轮发动机连接的发电机的电力需求的增加/减少而增加/减少第一气流的程序。

公开(公告)号：US20070175223A1

公开(公告)日：2007-08-02

申请号：US11345950

申请日：2006-02-02

Applicant: Chellappa Balan ,  Karl Sheldon

Inventor： Chellappa Balan ,  Karl Sheldon

IPC: F02C7/32

CPC classification number: B64D41/00 ,  B64D2013/0611 ,  B64D2041/002 ,  F02C7/32 ,  F05D2220/50

Abstract: A non-aircraft-propelling auxiliary gas turbine engine installable in an aircraft having a cabin adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor having an inlet, wherein the inlet is adapted to receive pressurized air from the cabin. A method for operating a non-aircraft-propelling auxiliary gas turbine engine of an aircraft includes providing pressurized air from the cabin of the aircraft to an inlet of a compressor of the auxiliary gas turbine engine. The method includes providing compressed air from the compressor to a combustor of the auxiliary gas turbine engine and includes providing combustion gases from the combustor to a turbine of the auxiliary gas turbine engine, wherein the turbine is mechanically coupled to the compressor.

Abstract translation: 可安装在具有适于加压的舱室的飞行器中的非飞机推进辅助燃气涡轮发动机。 辅助燃气涡轮发动机包括具有入口的辅助燃气涡轮发动机压缩机，其中入口适于从舱室接收加压空气。 用于操作飞行器的非飞机推进辅助燃气涡轮发动机的方法包括将来自飞机的舱室的加压空气提供给辅助燃气涡轮发动机的压缩机的入口。 该方法包括将压缩空气从压缩机提供给辅助燃气涡轮发动机的燃烧器，并且包括将来自燃烧器的燃烧气体提供给辅助燃气涡轮发动机的涡轮机，其中涡轮机械地联接到压缩机。

公开(公告)号：US20070234731A1

公开(公告)日：2007-10-11

申请号：US11398108

申请日：2006-04-05

Applicant: Karl Sheldon ,  John Turco

Inventor： Karl Sheldon ,  John Turco

IPC: F02C7/32

CPC classification number: B64D41/00 ,  B64D2033/0213 ,  F01D13/02 ,  F05D2220/50 ,  Y10S62/05

Abstract: A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. The outlets of the system turbine and the system compressor are fluidly connectable to the inlet of the compressor of the auxiliary gas turbine engine. A method includes providing compressed air from an aircraft to an inlet of a system turbine mechanically coupled to a system compressor. The method includes providing atmospheric air to an inlet of the system compressor. The method includes providing the inlet of the compressor of an auxiliary gas turbine engine with air from an outlet of the system turbine and with air from an outlet of the system compressor.

Abstract translation: 一种用于向飞行器的辅助燃气涡轮发动机的压缩机提供空气的系统。 系统涡轮机具有适于接收来自飞行器的压缩空气的入口。 系统压缩机机械耦合到系统涡轮机并且具有适于接收空气的入口。 系统涡轮机和系统压缩机的出口可流体地连接到辅助燃气涡轮发动机的压缩机的入口。 一种方法包括将来自飞行器的压缩空气提供给机械耦合到系统压缩机的系统涡轮机的入口。 该方法包括向系统压缩机的入口提供大气。 该方法包括向辅助燃气涡轮发动机的压缩机的入口提供来自系统涡轮机的出口的空气和来自系统压缩机的出口的空气。

公开(公告)号：US20070240426A1

公开(公告)日：2007-10-18

申请号：US11402477

申请日：2006-04-12

Applicant: Herman Wiegman ,  Karl Sheldon ,  John Turco ,  William Carlson

Inventor： Herman Wiegman ,  Karl Sheldon ,  John Turco ,  William Carlson

IPC: F02C9/00

CPC classification number: F02C9/00 ,  F02C9/18 ,  F05D2260/80 ,  F05D2270/101

Abstract: A controller for operating a gas turbine engine, wherein the gas turbine engine is installable in an installation platform, wherein the gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor. The controller includes a program which instructs the controller to run a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions and installation platform operating conditions. The controller also is programmed to calculate a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. A method for operating a gas turbine engine installed in an aircraft includes running a computer dynamic model of the engine and calculating a dynamic limit on mechanical power extraction from a shaft of the engine based at least on the running of the model.

Abstract translation: 一种用于操作燃气涡轮发动机的控制器，其中所述燃气涡轮发动机可安装在安装平台中，其中所述燃气涡轮发动机包括压缩机，涡轮机以及将所述涡轮连接到所述压缩机的轴。 控制器包括指示控制器运行燃气涡轮发动机的计算机动态模型的程序，其中计算机动态模型具有包括发动机操作条件和安装平台操作条件的输入。 控制器还被编程为至少基于燃气涡轮发动机的计算机动力学模型的运行来计算来自轴的机械功率提取的动态极限。 用于操作安装在飞行器中的燃气涡轮发动机的方法包括运行发动机的计算机动力学模型并且至少基于模型的运行来计算来自发动机的轴的机械功率提取的动态极限。