FUEL INJECTORS AND STAGED FUEL INJECTION SYSTEMS IN GAS TURBINES

• Main Author: LACY BENJAMIN PAUL
• Format: Patent
• Language: English; Japanese
• Published: 29.06.2017
• Subjects: BLASTING; COMBUSTION APPARATUS; COMBUSTION PROCESSES; ENGINE PLANTS IN GENERAL; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS; HEATING; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

PROBLEM TO BE SOLVED: To provide fuel injectors and staged fuel injection systems in gas turbines.SOLUTION: There is provided a gas turbine that includes a row of circumferentially spaced stator blades in a turbine. Each of the stator blades may include an airfoil defined between a concave pressure side face and a laterally opposed convex suction side face. At least one of the stator blades within the row may include a fuel injector that includes: a transverse nozzle extending through the airfoil between an inlet formed through the pressure side face and an outlet formed through the suction side face of the airfoil; and a fuel channel formed through the airfoil of the stator blade, the fuel channel having an upstream end, at which an inlet port fluidly connects the fuel channel to a fuel supply, and a downstream end, at which an outlet port fluidly connects the fuel channel to the transverse nozzle.SELECTED DRAWING: Figure 1 【課題】ガスタービンにおける燃料噴射器および段階的燃料噴射システムを提供する。【解決手段】タービンに円周方向離隔静翼列を備えたガスタービンである。静翼はそれぞれ、凹状の圧力側面と横方向に対向する凸状の吸引側面との間に規定されたエーロフォイルを具備していてもよい。列内の静翼のうちの少なくとも１つは、エーロフォイルの圧力側面を通して形成された入口と吸引側面を通して形成された出口との間でエーロフォイルを通って延びた横断ノズルと、静翼のエーロフォイルを通して形成された燃料チャネルであり、入口ポートが燃料チャネルを燃料供給に流体接続する上流端および出口ポートが燃料チャネルを横断ノズルに流体接続する下流端を有する、燃料チャネルと、を具備する燃料噴射器を備えていてもよい。【選択図】図１