Aerodynamic method to reduce noise level in gas turbines

Details Aerodynamic method to reduce noise level in gas turbines Aerodynamic method to reduce noise level in gas turbines

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 9/04 (2006.01) F23R 3/02 (2006.01)

Patent

CA 2503139

A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

L'invention concerne un procédé et un dispositif pour découpler l'atténuation et la variation de pression d'une chambre de combustion de l'atténuation et de la variation de pression d'une turbine dans un moteur à turbine à gaz. Le moteur comprend: un compresseur, une chambre de combustion, et une turbine qui produit un flux de gaz chaud et l'envoie de la chambre de combustion à la turbine. Un dispositif de déclenchement aérodynamique, disposé dans au moins une paroi de la chambre de combustion ou un anneau intérieur de la grille de l'aube directrice, est adapté pour émettre des jets d'air comprimé d'orifices d'écoulement croisé vers le débit de gaz chaud provenant de la chambre de combustion. Les jets d'air émanant des orifices d'écoulement croisé augmentent la turbulence et équilibrent la répartition de la température en plus de découpler l'atténuation et les variations de pression entre la chambre de combustion et la turbine.

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