GAS TURBINE SYSTEM

• Main Authors: MASUTANI MINORU, AOYAMA KUNIAKI
• Format: Patent
• Language: English; Japanese
• Published: 31.10.2019
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

To cool a turbine while restraining a decrease in efficiency.SOLUTION: A turbine cooling system 80 comprises: a first blade inside flow passage C1 and a second blade inside flow passage C2 radially penetrating the inside of a stator blade 36A; a rotating shaft inside flow passage C3 connecting the first blade inside flow passage C1 and the second blade inside flow passage C2 in a rotating shaft 31; a turbine outside flow passage C5 connecting the first blade inside flow passage C1 and the second blade inside flow passage C2; a boost compressor 83 for circulating cooling air through the first blade inside flow passage C1, the rotating shaft inside flow passage C3, the second blade inside flow passage C2, and the turbine outside flow passage C5 in this order; and a cooling part 81 for cooling the cooling air.SELECTED DRAWING: Figure 2 【課題】効率の低下を抑制しつつ、タービンを冷却する。【解決手段】タービン冷却系統８０は、静翼３６Ａ内を径方向に貫通する第一翼内流路Ｃ１、及び第二翼内流路Ｃ２と、回転軸３１内で第一翼内流路Ｃ１と第二翼内流路Ｃ２とを接続する回転軸内流路Ｃ３と、第一翼内流路Ｃ１と第二翼内流路Ｃ２とを接続するタービン外流路Ｃ５と、第一翼内流路Ｃ１、回転軸内流路Ｃ３、第二翼内流路Ｃ２およびタービン外流路Ｃ５の順で冷却空気を流通させるブースト圧縮機８３と、冷却空気を冷却する冷却部８１と、を有する。【選択図】図２