Patents by Inventor Gary Craig Wollenweber
Gary Craig Wollenweber has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10392117Abstract: A system and method for monitoring icing conditions that are suitable ice formation on an aircraft and propulsion system. The system includes instrumentation that instantaneously detects ambient humidity, ambient temperature and ambient pressure. The sensed information is transmitted to a controller that evaluates the information to determine whether certain pressure, temperature and humidity criteria are favorable for icing and, declaring icing conditions. The system also includes an aircraft engine-mounted ice mitigation system. When conditions for ice formation are favorable, the controller either informs the pilot that conditions for ice formation are favorable or automatically activates the ice mitigation system, or both. The pilot optionally may inactivate the ice mitigation system. When sensed conditions indicate that conditions for ice formation are not favorable, the controller determines whether the ice mitigation system is activated and inactivates the system if activated.Type: GrantFiled: September 23, 2016Date of Patent: August 27, 2019Assignee: General Electric CompanyInventor: Gary Craig Wollenweber
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Publication number: 20180086471Abstract: A system and method for monitoring icing conditions that are suitable ice formation on an aircraft and propulsion system. The system includes instrumentation that instantaneously detects ambient humidity, ambient temperature and ambient pressure. The sensed information is transmitted to a controller that evaluates the information to determine whether certain pressure, temperature and humidity criteria are favorable for icing and, declaring icing conditions. The system also includes an aircraft engine-mounted ice mitigation system. When conditions for ice formation are favorable, the controller either informs the pilot that conditions for ice formation are favorable or automatically activates the ice mitigation system, or both. The pilot optionally may inactivate the ice mitigation system. When sensed conditions indicate that conditions for ice formation are not favorable, the controller determines whether the ice mitigation system is activated and inactivates the system if activated.Type: ApplicationFiled: September 23, 2016Publication date: March 29, 2018Inventor: Gary Craig WOLLENWEBER
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Patent number: 9695750Abstract: A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.Type: GrantFiled: November 26, 2013Date of Patent: July 4, 2017Assignee: General Electric CompanyInventor: Gary Craig Wollenweber
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Publication number: 20150300260Abstract: A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.Type: ApplicationFiled: November 26, 2013Publication date: October 22, 2015Applicant: GENERAL ELECTRIC COMPANYInventor: Gary Craig WOLLENWEBER
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Patent number: 8117827Abstract: A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine.Type: GrantFiled: March 16, 2009Date of Patent: February 21, 2012Assignee: General Electric CompanyInventors: Gary Craig Wollenweber, John B. Turco
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Publication number: 20090173056Abstract: A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine.Type: ApplicationFiled: March 16, 2009Publication date: July 9, 2009Inventors: Gary Craig Wollenweber, John B. Turco
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Patent number: 7549291Abstract: A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine.Type: GrantFiled: January 10, 2005Date of Patent: June 23, 2009Assignee: General Electric CompanyInventors: Gary Craig Wollenweber, John B. Turco
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Patent number: 7219499Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas turbine engine upstream from the core engine turbine, and channeled to the auxiliary engine for generating power.Type: GrantFiled: September 6, 2006Date of Patent: May 22, 2007Assignee: General Electric CompanyInventors: John B. Turco, Gary Craig Wollenweber
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Patent number: 7121078Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas turbine engine upstream from the core engine turbine, and channeled to the auxiliary engine for generating power.Type: GrantFiled: March 12, 2004Date of Patent: October 17, 2006Assignee: General Electric CompanyInventors: John B. Turco, Gary Craig Wollenweber
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Patent number: 6968674Abstract: A method facilitates operating a gas turbine engine assembly including a propelling engine and an auxiliary power engine. The method comprises channeling a portion of airflow entering an inlet to the propelling gas turbine engine through a fan assembly and a bypass duct such that the air bypasses the core engine, and channeling a portion of airflow from the bypass duct towards the auxiliary power engine.Type: GrantFiled: January 28, 2003Date of Patent: November 29, 2005Assignee: General Electric CompanyInventor: Gary Craig Wollenweber
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Publication number: 20040168427Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas turbine engine upstream from the core engine turbine, and channeled to the auxiliary engine for generating power.Type: ApplicationFiled: March 12, 2004Publication date: September 2, 2004Inventors: John B. Truco, Gary Craig Wollenweber
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Publication number: 20040144096Abstract: A method facilitates operating a gas turbine engine assembly including a propelling engine and an auxiliary power engine. The method comprises channeling a portion of airflow entering an inlet to the propelling gas turbine engine through a fan assembly and a bypass duct such that the air bypasses the core engine, and channeling a portion of airflow from the bypass duct towards the auxiliary power engine.Type: ApplicationFiled: January 28, 2003Publication date: July 29, 2004Inventor: Gary Craig Wollenweber