JPS6067299A - Icing preventive device for aircraft - Google Patents
Icing preventive device for aircraftInfo
- Publication number
- JPS6067299A JPS6067299A JP17410483A JP17410483A JPS6067299A JP S6067299 A JPS6067299 A JP S6067299A JP 17410483 A JP17410483 A JP 17410483A JP 17410483 A JP17410483 A JP 17410483A JP S6067299 A JPS6067299 A JP S6067299A
- Authority
- JP
- Japan
- Prior art keywords
- heat pipe
- heat
- aircraft
- icing
- connect
- 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
Landscapes
- Body Structure For Vehicles (AREA)
- Suspension Of Electric Lines Or Cables (AREA)
- Window Of Vehicle (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
本発明はジェットエンジンの排気熱を利用して航空機の
着氷を防止する装置に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a device for preventing icing on an aircraft using exhaust heat from a jet engine.
従来、航空機の飛行中における主翼及び尾翼の前縁、エ
ンジン吸気ダクトのリップ部、ピトー管、アンテナ支柱
、ドレン孔等の着氷を防止するため、ジェットエンジン
のコンプレッサで圧縮された高温高圧の抽気を航空機の
着氷部位にダクトで導き、噴気させて該部位を加熱し着
氷を防止していた。Conventionally, high-temperature, high-pressure bleed air compressed by a jet engine compressor has been used to prevent icing on the leading edges of the main wings and tail, the lips of engine intake ducts, pitot tubes, antenna struts, drain holes, etc. during aircraft flight. was guided through a duct to the icing area of the aircraft, and the steam was generated to heat the area and prevent icing.
しかし、かかる着氷防止手段は燃料の燃焼に必要な抽気
を減少させる結果、燃料消費量を節約するという近年の
要請に応えるものではなかった。However, such icing prevention means reduce the amount of air bleed required for fuel combustion, and as a result do not meet the recent demand for saving fuel consumption.
現在の航空機、特に民間機は燃料を節約するために非電
な枝術的努力を行っており、例えばＦ Ｍ Ｓ （ＦＩ
ｉｇｌ＋ｔ Ｍａｎａｇｅｍｅｎｔ Ｓｙｓｔｅｍ）
という高価な装置によって最適な高度、速度、エンジン
出力等を設定し燃料の節約を行っているが、このシステ
ムで節約できる燃料量は１〜２％程度であり、また、前
述した抽気利用の従来の防水手段の燃料消費量に占める
割合は２〜４％であるが、この割合を減少させようと試
みても、防水に必要な抽気量は着氷量から自動的に決ま
ってくるものであるから、燃料節約の見地から防水のた
めに使用される抽気量の減量をはかることはできず、し
たがって、従来の防水手段においては更に燃料消費量を
節約することは困難であ つ ノこ・
本発明は上述の現状に鑑み、ジェットエンジンの抽気を
利用することなく、燃料の燃焼後の排気を利用すること
により燃焼に参加する充分な抽気量を確保し燃料滴′Ｒ
Ｎの節約を可能にして従来の欠点を除去したもので、以
下本発明の実施例を左舷側主翼前縁の場合について説明
すると、
左舷側主翼１に取付けたジェットエンジン２の排気ノズ
ル３の内周面にピー１−パイプの蒸発９１Ｓ ’４を取
付け、該蒸発部４に第２図に示す如き接続部５を介して
開閉弁６を有する導入ヒートパイプ７を着脱可能に接続
して蓄熱器８に連結し、該蓄熱器８にヒートパイプ９を
接続し、主翼前縁着氷部位１０に該ヒートパイプ９の凝
縮部１１を取付りる。そしそ右舷側主翼にも同様の防水
手段が取イ（」げられ、左舷側主翼に取イ］けたｇ７ｆ
、％器８と右舷側主翼に取イ１けた蓄熱器とはヒートパ
イプ１２で接続されている。Modern aircraft, especially commercial aircraft, employ non-electrical branch efforts to conserve fuel, such as FMS (FI
igl+t Management System)
The system saves fuel by setting the optimum altitude, speed, engine output, etc. using an expensive device called ``Bleed Air'', but the amount of fuel saved by this system is only about 1 to 2%, Waterproofing measures account for 2 to 4% of fuel consumption, but even if attempts are made to reduce this percentage, the amount of air bleed required for waterproofing is automatically determined from the amount of ice accretion. Therefore, it is not possible to reduce the amount of bleed air used for waterproofing from the standpoint of fuel conservation, and therefore it is difficult to further reduce fuel consumption with conventional waterproofing methods. In view of the above-mentioned current situation, the present invention utilizes the exhaust air after combustion of the fuel without using the bleed air of the jet engine, thereby securing a sufficient amount of bleed air to participate in combustion, and reducing the amount of fuel droplets 'R.
This makes it possible to save N and eliminates the drawbacks of the conventional technology.The embodiment of the present invention will be explained below with reference to the leading edge of the port side main wing. A P1-pipe evaporator 91S'4 is attached to the circumferential surface, and an introduction heat pipe 7 having an on-off valve 6 is detachably connected to the evaporator section 4 through a connecting section 5 as shown in FIG. 8, a heat pipe 9 is connected to the heat storage device 8, and a condensing section 11 of the heat pipe 9 is attached to the icing region 10 of the leading edge of the main wing. Similar waterproofing measures were also installed on the starboard main wing, and the g7f was installed on the port side main wing.
, the percentage unit 8 and a heat storage device located on the starboard side main wing are connected by a heat pipe 12.
なお、導入ヒートパイプの数量は所要熱輸送量によって
決定されるものである。Note that the number of introduced heat pipes is determined by the required amount of heat transport.
したがって、本発明においては、ジェットエンジンの排
気ノズル３から排出される排気熱をヒートパイプの蒸発
部４で吸収し、導入ヒートパイプ７でその排気熱を蓄熱
器８に導入する。Therefore, in the present invention, the exhaust heat discharged from the exhaust nozzle 3 of the jet engine is absorbed by the evaporator section 4 of the heat pipe, and the exhaust heat is introduced into the heat storage device 8 by the introduction heat pipe 7.
蓄熱器８に貯えた熱をヒートパイプ９によって凝縮部１
１に送り、主翼前縁着氷部位１ ｆＪを加ｉ４％ ｌ、
て着氷を防止するものである。The heat stored in the heat storage device 8 is transferred to the condensing section 1 by the heat pipe 9.
1, add 1 fJ to main wing leading edge icing area, i4% l,
This prevents icing.
また、片舷のジェットエンジン又は複数のジエン１ヘエ
ンジンの１つが不時停止した場合には、正常に作動して
いるジェンＩ・エンジンの蓄熱器からヒートパイプ１２
を介して不時停止のジェットエンジンの蓄熱器に熱を導
入してヒートパイプ凝縮部による防水作用を継続させる
ことができるから、すべてのエンジンが停止しない限り
、ピー１−パイプによる防水機能は支障なく遂行される
。In addition, in the event of an unforeseen stoppage of one jet engine or one of the engines, the heat pipe 12 is connected to the heat storage of the normally operating Gen I engine.
Since it is possible to continue the waterproofing effect of the heat pipe condensation section by introducing heat into the heat storage unit of the jet engine that has suddenly stopped, the waterproofing function of the P1-pipe will not be affected unless all engines are stopped. It is carried out without any problems.
更にまた、防水を必要としない場合には開閉弁６の閉弁
操作によりヒートパイプ７による排気熱の導入を遮断し
、エンジン交換時には接続部５でヒートパイプ蒸発部４
と導入ヒートパイプ７とを着脱して容易に交換作業を行
うことが可能である。Furthermore, when waterproofing is not required, the introduction of exhaust heat by the heat pipe 7 is shut off by closing the on-off valve 6, and when the engine is replaced, the heat pipe evaporation section 4 is connected to the connection section 5.
It is possible to easily perform replacement work by attaching and detaching the heat pipe 7 and the introduction heat pipe 7.
以上述べた如く、本発明はエンジン抽気を使用せず排気
熱を熱源に利用するため、燃料の燃焼に必要且つ充分な
抽気量が確保されて消費燃料の節約をはかって省エネル
ギー化の実現が可能となり、また、ヒートパイプは特別
の点検を必要としないので機体整備上格別の労力を不要
とし、更にヒートパイプの凝縮部は着氷部位の長手方向
の放熱温度を一定にするので、従来の噴気加熱に比し着
氷部位は均一に加熱され、防水効率を一層向上させるこ
とが可能になる等、多（のぼれた効果をイｆするもので
ある。As described above, since the present invention uses exhaust heat as a heat source without using engine bleed air, a sufficient amount of bleed air necessary for fuel combustion is secured, and it is possible to save fuel consumption and realize energy savings. In addition, heat pipes do not require special inspections, so no special effort is required for aircraft maintenance.Furthermore, the condensing part of the heat pipe keeps the heat dissipation temperature constant in the longitudinal direction of the icing area, so it is no longer necessary to use conventional fumarole. Compared to heating, the icy area is heated more uniformly, making it possible to further improve waterproofing efficiency, and so on.
図面ば本発明の実施例を示し、第１図は左舷側主翼に取
付けた本発明の概略斜視図、第２図は左舷側主翼に取付
りた本発明の概略平面図、第３図は主翼の要部断面図で
ある。
２・・・ジェットエンジン ３・・・排気ノズル４・・
・ピー１−パイプ蒸発部 ５・・・接続部６・・・開閉
弁 ７・・・導入ヒートパイプ８・・・蓄熱器 ９・・
・ヒートパイプ１０・・・着氷部位 １１・・・ヒート
パイプ凝縮部代理人 弁理士 祐用尉−外１名The drawings show an embodiment of the present invention; FIG. 1 is a schematic perspective view of the present invention attached to the port side main wing, FIG. 2 is a schematic plan view of the present invention attached to the port side main wing, and FIG. 3 is the main wing. FIG. 2...Jet engine 3...Exhaust nozzle 4...
・P1-Pipe evaporation section 5...Connection section 6...Opening/closing valve 7...Introduction heat pipe 8...Regenerator 9...
・Heat pipe 10...Icing part 11...Heat pipe condensing section agent Patent attorney Yuyosuke - 1 other person
Claims (2)
の蒸発部を取付け、該ヒートパイプ蒸発部に開閉弁を有
する導入ヒートパイプを着脱可能に接続して蓄熱器に連
結し、該蓄熱器とヒートパイプの凝縮部となる航空機の
着氷部位との間にヒートパイプを配管した航空機の着氷
防止装置。(1) Attach the evaporator section of the heat pipe to the exhaust nozzle of the jet engine, removably connect an introduction heat pipe with an on-off valve to the heat pipe evaporator section, and connect it to the heat storage device. An aircraft icing prevention device that has a heat pipe installed between the condensing part and the icing part of the aircraft.
トパイプの蒸発部を取付け、該夫々のヒートパイプ蒸発
部に開閉弁を有する導入ヒートパイプを着ＪＪＱ可能に
接続して蓄熱器に連結し、夫々のＭ熱器をヒートパイプ
で接続し、少くとも一つの蓄熱器とヒートパイプの凝縮
部となる航空機の着氷部位との間にヒートパイプを配管
した航空機の着氷防止装置。(2) Attach an evaporation section of a heat pipe to each of the exhaust nozzles of a plurality of jet engines, and connect an inlet heat pipe having an on-off valve to each of the heat pipe evaporation sections so as to connect it to a heat storage device. An anti-icing device for an aircraft, in which two M heaters are connected by a heat pipe, and the heat pipe is piped between at least one heat storage device and an icing part of the aircraft that serves as a condensation part of the heat pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17410483A JPS6067299A (en) | 1983-09-22 | 1983-09-22 | Icing preventive device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17410483A JPS6067299A (en) | 1983-09-22 | 1983-09-22 | Icing preventive device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6067299A true JPS6067299A (en) | 1985-04-17 |
Family
ID=15972713
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17410483A Pending JPS6067299A (en) | 1983-09-22 | 1983-09-22 | Icing preventive device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6067299A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007064228A (en) * | 2005-09-01 | 2007-03-15 | General Electric Co <Ge> | Device operating gas turbine engine |
| JP2008057538A (en) * | 2006-08-31 | 2008-03-13 | General Electric Co <Ge> | Heat pipe-based cooling apparatus for turbine engine |
| JP2012507675A (en) * | 2008-10-31 | 2012-03-29 | ゼネラル・エレクトリック・カンパニイ | Bearing assembly and method for controlling fluid flow in a conduit |
-
1983
- 1983-09-22 JP JP17410483A patent/JPS6067299A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007064228A (en) * | 2005-09-01 | 2007-03-15 | General Electric Co <Ge> | Device operating gas turbine engine |
| JP2008057538A (en) * | 2006-08-31 | 2008-03-13 | General Electric Co <Ge> | Heat pipe-based cooling apparatus for turbine engine |
| JP2012507675A (en) * | 2008-10-31 | 2012-03-29 | ゼネラル・エレクトリック・カンパニイ | Bearing assembly and method for controlling fluid flow in a conduit |
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