FUEL NOZZLE FOR GAS TURBINE ENGINE

• Main Authors: THOMSEN DUANE DOUGLAS, PATEL NAYAN VINODBHAI
• Format: Patent
• Language: English; Japanese
• Published: 29.09.2016
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION APPARATUS; COMBUSTION ENGINES; COMBUSTION PROCESSES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; GAS-TURBINE PLANTS; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MECHANICAL ENGINEERING; WEAPONS

PROBLEM TO BE SOLVED: To provide a staged fuel nozzle for a gas turbine engine.SOLUTION: A fuel nozzle apparatus includes: an annular outer body 32, with an exterior surface having a plurality of openings 114; a main injection ring 24 inside the outer body 32, the main injection ring 24 including a circumferential main fuel gallery 100 and a plurality of main fuel orifices 102 communicating with the main fuel gallery 100; a venturi 90 inside the main injection ring 24; an annular splitter 28 inside the venturi 90, the annular splitter 28 including inner and outer walls separated from each other and defining a splitter cavity 64, and a plurality of discharge holes 66 communicating with the splitter cavity 64; an array of outer swirl vanes 98 extending between the venturi 90 and the splitter 28; a pilot fuel injector 18 inside the splitter 28; and an array of inner swirl vanes 68 extending between the splitter 28 and the pilot fuel injector 18.SELECTED DRAWING: Figure 1 【課題】ガスタービンエンジン用の段階式燃料ノズルを提供する。【解決手段】燃料ノズル装置は、複数の開口１１４を有する外部表面を備える環状外側本体３２と、外側本体３２内の主噴射リング２４であって、周方向主油溜室１００と、主油溜室１００と連通する複数の主燃料オリフィス１０２とを含む主噴射リング２４と、主噴射リング２４内のベンチュリ９０と、ベンチュリ９０内の環状スプリッタ２８であって、互いに離間してスプリッタキャビティ６４を画成する内側壁および外側壁と、スプリッタキャビティ６４に連通する複数の排出孔６６とを有する環状スプリッタ２８と、ベンチュリ９０とスプリッタ２８との間に延在する外側スワールベーン９８の配列と、スプリッタ２８内のパイロット燃料噴射器１８と、スプリッタ２８とパイロット燃料噴射器１８との間に延在する内側スワールベーン６８の配列とを含む。【選択図】図１