Patent number 8522521 is assigned to
The following quote was obtained by the news editors from the background information supplied by the inventors: "The present invention relates to gas turbine engines, and in particular, to air turbine starters on gas turbine engines. Gas turbine engines typically have at least one spool that includes a compressor and a turbine. When a gas turbine engine is burning fuel and operating, the spool rotates at a high speed without further assistance. However, when a gas turbine engine is started, the spool typically needs assistance to begin rotation. Various starters have been devised to start the spool rotating.
"In some gas turbine engines, an air turbine starter is used to start rotation of the spool. The air turbine starter has a turbine which is typically connected to the spool via gearing. Compressed air is blown over the turbine of the air turbine starter, which causes the spool to rotate and start the gas turbine engine. After starting the gas turbine engine, the air turbine starter typically provides no useful function until the gas turbine engine needs to be started again. In the meantime, the air turbine starter just adds undesirable weight to a gas turbine engine, which is especially undesirable on an aircraft.
"Gas turbine engines also typically have various components, such as gears and bearings, which benefit from lubrication and cooling. An oil supply system supplies oil, or another lubricating liquid, to and from the components to lubricate and cool the components. This oil is typically cooled by a heat exchanger positioned in a gas flow path. If the gas flow path has a relatively slow air flow, the heat exchanger typically needs to be relatively large and bulky to achieve the desired amount of cooling. A relatively large heat exchanger undesirably increases the weight of the aircraft. In gas turbine engines where the heat exchanger is positioned in a bypass flow stream of the engine's propulsion fan, the heat exchanger can also reduce overall thrust output."
In addition to the background information obtained for this patent, VerticalNews journalists also obtained the inventor's summary information for this patent: "According to the present invention, an air turbine starter assembly includes a starter turbine housing having a turbine gas flow path and a fan gas flow path, and a shaft rotatable with respect to the starter turbine housing. A plurality of turbine blades are connected to the shaft. A plurality of fan blades are also connected to the shaft.
"Another embodiment of the present invention includes a method of operating a starter turbine for use on a gas turbine engine. The method includes flowing compressed gas through a turbine gas flow path over turbine blades attached to a shaft to rotate the shaft, blowing air through a fan gas flow path via fan blades attached to the shaft, and cooling lubricating liquid via a heat exchanger positioned in the fan gas flow path."
URL and more information on this patent, see: Dyer,
Keywords for this news article include: Aerospace and Defense Companies,
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