To reduce heat transferred to an optical component, in a laser ignition type engine.SOLUTION: A laser ignition type engine 100 comprises at least one optical component 3a, 3b, 3c that is arranged along an axial line X toward a combustion chamber 12 and guides laser light to the combustion chamber 12, and a housing 5 that accommodates the at least one optical component 3a, 3b, 3c. The housing 5 includes a first accommodation chamber 52 that accommodates the at least one optical component 3a, 3b, 3c, and an oxidant flow path 55 that is fluidly connected to the combustion chamber 12 and supplies an oxidant to the combustion chamber 12. The oxidant flow path 55 is located outside the first accommodation chamber 52 in a radial direction based on the axial line X, and includes a portion that overlaps with the first accommodation chamber 52 in an axial direction parallel to the axial line X.SELECTED DRAWING: Figure 1
【課題】レーザ点火式エンジンにおいて、光学部品に伝わる熱を低減すること。【解決手段】レーザ点火式エンジン100は、燃焼室12に向う軸線Xに沿って配置され、レーザ光を燃焼室12に導く少なくとも1つの光学部品3a,3b,3cと、少なくとも1つの光学部品3a,3b,3cを収容するハウジング5と、を備える。ハウジング5は、少なくとも1つの光学部品3a,3b,3cを収容する第1収容室52と、燃焼室12と流体連通し、燃焼室12に酸化剤を供給する酸化剤流路55と、を含む。酸化剤流路55は、軸線Xを基準とする径方向において第1収容室52の外側に位置し、かつ、軸線Xと平行な軸線方向において第1収容室52と重複する部分を含む。【選択図】図1
LASER IGNITION TYPE ENGINE
レーザ点火式エンジン
11.10.2024
Patent
Elektronische Ressource
Japanisch
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS |
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