Gas turbine engine having a flow control surface with a cooling conduit

The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational...

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Bibliographische Detailangaben
Hauptverfasser:	Pritchard, Byron Andrew, Jothiprasad, Giridhar, Bourassa, Corey, Atsuchi, Satoshi, Dede, Mehmet Muhittin, Krammer, Erich Alois, Otta, Shourya Prakash
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS PERFORMING OPERATIONS PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS SEPARATION STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.