JPS6261945U - - Google Patents
Info
- Publication number
- JPS6261945U JPS6261945U JP15285585U JP15285585U JPS6261945U JP S6261945 U JPS6261945 U JP S6261945U JP 15285585 U JP15285585 U JP 15285585U JP 15285585 U JP15285585 U JP 15285585U JP S6261945 U JPS6261945 U JP S6261945U
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- fuel
- shaft
- compressor
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000446 fuel Substances 0.000 claims description 12
- 238000002485 combustion reaction Methods 0.000 claims description 4
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
第1図はジエツトエンジンの空気圧縮機の後部
より燃料を燃料圧縮機内部へ燃料を取り入れるジ
エツトエンジンの側面切断面図。第2図は空気圧
縮機の外周より燃料を燃料圧縮機内部へ燃料を取
り入れるジエツトエンジンの側面切断面図、第3
図はジエツトタービンの正面図である。
1は空気圧縮機、2は燃料圧縮機、3は空気口
、4はタービンの軸の燃料圧縮機、5はタービン
の軸、6は燃焼室、7は後部燃焼室、8はタービ
ン、9は燃料パイプ、10は燃料通過部、11は
燃料通過用箇。
FIG. 1 is a side sectional view of a jet engine in which fuel is taken into the fuel compressor from the rear of the air compressor of the jet engine. Figure 2 is a side cross-sectional view of a jet engine that takes fuel into the fuel compressor from the outer periphery of the air compressor.
The figure is a front view of the jet turbine. 1 is an air compressor, 2 is a fuel compressor, 3 is an air port, 4 is a fuel compressor on the shaft of a turbine, 5 is a shaft of a turbine, 6 is a combustion chamber, 7 is a rear combustion chamber, 8 is a turbine, 9 is a A fuel pipe, 10 is a fuel passage part, and 11 is a fuel passage part.
Claims (1)
縮機を設け、又、タービンの軸の内部を空洞化さ
せ、タービンの軸に燃料圧縮機を設ける。 ジエツトエンジンの後部にも燃焼室を設け圧縮
した燃料はタービンの軸内部を通つて後部燃焼室
へ送られる。[Claims for Utility Model Registration] A fuel compressor is provided inside the air compressor of the jet engine, and the inside of the shaft of the turbine is hollowed out, and the fuel compressor is provided on the shaft of the turbine. A combustion chamber is also provided at the rear of the jet engine, and the compressed fuel is sent to the rear combustion chamber through the inside of the turbine shaft.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15285585U JPS6261945U (en) | 1985-10-04 | 1985-10-04 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15285585U JPS6261945U (en) | 1985-10-04 | 1985-10-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS6261945U true JPS6261945U (en) | 1987-04-17 |
Family
ID=31071214
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP15285585U Pending JPS6261945U (en) | 1985-10-04 | 1985-10-04 |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS6261945U (en) |
-
1985
- 1985-10-04 JP JP15285585U patent/JPS6261945U/ja active Pending
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