JPH04203465A - Engine using hydrogen fuel - Google Patents
Engine using hydrogen fuelInfo
- Publication number
- JPH04203465A JPH04203465A JP33677490A JP33677490A JPH04203465A JP H04203465 A JPH04203465 A JP H04203465A JP 33677490 A JP33677490 A JP 33677490A JP 33677490 A JP33677490 A JP 33677490A JP H04203465 A JPH04203465 A JP H04203465A
- Authority
- JP
- Japan
- Prior art keywords
- hydrogen
- hydrogen gas
- temperature
- combustion chamber
- high temperature
- 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
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 117
- 239000001257 hydrogen Substances 0.000 title claims abstract description 68
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 68
- 239000000446 fuel Substances 0.000 title claims description 13
- 238000002485 combustion reaction Methods 0.000 claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 17
- 239000000919 ceramic Substances 0.000 claims abstract description 7
- 239000007788 liquid Substances 0.000 claims description 29
- 229910052751 metal Inorganic materials 0.000 claims description 16
- 239000002184 metal Substances 0.000 claims description 16
- 230000002265 prevention Effects 0.000 claims description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract description 6
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 abstract description 6
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 abstract description 3
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 abstract description 3
- 229910052782 aluminium Inorganic materials 0.000 abstract description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 abstract description 3
- 229910052804 chromium Inorganic materials 0.000 abstract description 3
- 239000011651 chromium Substances 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 3
- 229910052759 nickel Inorganic materials 0.000 abstract description 3
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 abstract description 3
- 229910052727 yttrium Inorganic materials 0.000 abstract description 3
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 abstract description 3
- 230000003449 preventive effect Effects 0.000 abstract 2
- 238000005507 spraying Methods 0.000 abstract 2
- 238000001816 cooling Methods 0.000 description 11
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 10
- 239000000567 combustion gas Substances 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 2
- 239000010931 gold Substances 0.000 description 2
- 229910052737 gold Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003763 carbonization Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 238000004544 sputter deposition Methods 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
Landscapes
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Ceramic Products (AREA)
Abstract
Description
【発明の詳細な説明】
［産業上の利用分野コ
本発明は、液体ロケットエンジンやエアターボラムジェ
ット等の水素燃料用エンジンに関するものである。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a hydrogen fuel engine such as a liquid rocket engine or an air turbo ramjet.
［従来の技術］
以下、従来の水素燃料用エンジンの一例として、液体ロ
ケットエンジンを第３図を用いて説明する。[Prior Art] A liquid rocket engine will be described below as an example of a conventional hydrogen fuel engine with reference to FIG.
図中１は液体ロケットエンンン本体、２は液体ロケット
エンジン本体ｌの燃焼室、３は燃焼室２の入側に形成さ
れた水素噴射器、４は燃焼室２の入側に形成された酸素
噴射器、５は燃焼室２の出側に形成されたノズル、６は
燃焼室２外周部に形成された冷却ジャケット（高温水素
ガス発生装置）、７はノズル５外周部に形成された冷却
ジャケット（高温水素ガス発生装置）、８は冷却ジャケ
ット６の水素噴射器３寄りの位置と冷却ジャケット７の
水素噴射器３寄りの位置とを接続する水素配管である。In the figure, 1 is the liquid rocket engine body, 2 is the combustion chamber of the liquid rocket engine body, 3 is the hydrogen injector formed on the inlet side of the combustion chamber 2, and 4 is the oxygen injector formed on the inlet side of the combustion chamber 2. Injector, 5 is a nozzle formed on the outlet side of the combustion chamber 2, 6 is a cooling jacket (high temperature hydrogen gas generator) formed on the outer periphery of the combustion chamber 2, 7 is a cooling jacket formed on the outer periphery of the nozzle 5 (High-temperature hydrogen gas generator) 8 is a hydrogen pipe connecting the position of the cooling jacket 6 near the hydrogen injector 3 and the position of the cooling jacket 7 near the hydrogen injector 3.
一方、９は液体水素用ターボポンプ、１０は液体酸素用
ターボポンプであり、前記液体水素用ターボポンプ９の
インペラ１２は、図示しない液体水素タンクと燃焼室２
外周の冷却ジャケット６の反水素噴射器３寄りの位置と
を接続する液体水素配管１３の途中に接続され、前記液
体酸素用ターボポンプ１０のインペラ１４は、図示しな
い液体酸素タンクと酸素噴射器４とを接続する液体水素
配管１５の途中に接続され、前記液体水素用ターボポン
プ９及び液体酸素用ターボポンプ１０のタービン１８．
１９はノズル５外周の冷却ジャケット７の反水素噴射器
３寄りの位置と水素噴射器３とを接続する高温水素ガス
配管２０の途中に順番に接続されている。On the other hand, 9 is a liquid hydrogen turbo pump, 10 is a liquid oxygen turbo pump, and the impeller 12 of the liquid hydrogen turbo pump 9 is connected to a liquid hydrogen tank (not shown) and a combustion chamber 2
The impeller 14 of the liquid oxygen turbo pump 10 is connected in the middle of the liquid hydrogen pipe 13 that connects the outer cooling jacket 6 to a position near the anti-hydrogen injector 3, and the impeller 14 of the liquid oxygen turbo pump 10 connects the liquid oxygen tank (not shown) with the oxygen injector The turbine 18 of the liquid hydrogen turbo pump 9 and the liquid oxygen turbo pump 10 is
19 are sequentially connected in the middle of a high-temperature hydrogen gas pipe 20 that connects the hydrogen injector 3 to a position of the cooling jacket 7 on the outer periphery of the nozzle 5 near the anti-hydrogen injector 3.
そして、図示しない液体水素タンクの液体水素は、液体
水素用ターボポンプ９のインペラ１２によって液体水素
配管１３を介して燃焼室２外周の冷却ジャケット６の反
水素噴射器３寄りの位置へ送給され、冷却ジャケット６
を流れて燃焼室２を冷却し、水素噴射器３寄りの位置か
ら水素配管８を通ってノズル５外周の冷却ジャケット７
の水素噴射器３寄りの位置へ送給され、冷却ジャケット
７を流れてノズル５を冷却する。The liquid hydrogen in the liquid hydrogen tank (not shown) is fed by the impeller 12 of the liquid hydrogen turbo pump 9 via the liquid hydrogen pipe 13 to a position near the anti-hydrogen injector 3 of the cooling jacket 6 on the outer periphery of the combustion chamber 2. , cooling jacket 6
It flows through the hydrogen pipe 8 from a position near the hydrogen injector 3 to the cooling jacket 7 around the nozzle 5.
The hydrogen is fed to a position near the hydrogen injector 3 and flows through the cooling jacket 7 to cool the nozzle 5.
燃焼室２とノズル５を冷却することにより熱交換して気
化された水素ガスは高温水素ガス配管２０から液体水素
用ターボポンプ９及び液体酸素用ターボポンプ１０のタ
ービン１８．１９を通って液体水素用ターボポンプ９及
び液体酸素用ターボポンプ１０を駆動し、水素噴射器３
へ送られ、液体酸素配管１５を通って酸素噴射器４へ送
られる液体酸素によって燃焼室２で燃焼され燃焼ガスが
ノズル５から噴射されることによって推力が発生される
。The hydrogen gas vaporized by heat exchange by cooling the combustion chamber 2 and the nozzle 5 passes from the high-temperature hydrogen gas pipe 20 to the turbines 18 and 19 of the liquid hydrogen turbo pump 9 and the liquid oxygen turbo pump 10, and becomes liquid hydrogen. The hydrogen injector 3 drives the turbo pump 9 for liquid oxygen and the turbo pump 10 for liquid oxygen.
The liquid oxygen sent to the oxygen injector 4 through the liquid oxygen piping 15 is combusted in the combustion chamber 2, and the combustion gas is injected from the nozzle 5, thereby generating thrust.
第４図は水素燃料用エンジンの他の実施例としてのエア
ターボラムジェットである。FIG. 4 shows an air turbo ramjet as another embodiment of the hydrogen fuel engine.
図中２１はエアターボラムジェット本体、２２はエアタ
ーボラムジェット本体２１の入側に設けられた空気取入
れ口、２３は空気取入れ口２２の出側に配設されたブリ
クーラ、２４はブリクーラ２３の出側に配設されたコン
プレッサ、２５はコンプレッサ２４の外周に配設され図
示しない駆動力伝達機構によってコンプレッサ２４と一
体的に回転可能なタービン、２６はコンプレッサ２４及
びタービン２５の出側に形成された燃焼室、２７は燃焼
室２６の出側外周に設けられた水素加熱器と呼ばれる高
温水素ガス発生装置、２８は燃焼室２６の出側に形成さ
れたノズルである。In the figure, 21 is an air turbo ramjet main body, 22 is an air intake provided on the inlet side of the air turbo ramjet main body 21, 23 is a pre-cooler provided on the outlet side of the air intake 22, and 24 is a pre-cooler 23. A compressor 25 is provided on the outlet side of the compressor 24, and a turbine 25 is provided on the outer periphery of the compressor 24 and is rotatable integrally with the compressor 24 by a driving force transmission mechanism (not shown). 27 is a high-temperature hydrogen gas generator called a hydrogen heater provided on the outer periphery of the outlet side of the combustion chamber 26, and 28 is a nozzle formed on the outlet side of the combustion chamber 26.
又、２９は図示しない液体水素タンクとブリクーラ２３
の入側とを接続する液体水素配管、３０はブリクーラ２
３の出側と高温水素ガス発生装置ｚ７の入側とを接続す
る低温水素ガス配管、３１は高温水素ガス発生装置２７
の出側とタービン入口マニホールド３２とを接続する高
温水素ガス配管、３３は空気、３４は燃焼ガスである。In addition, 29 is a liquid hydrogen tank and a pre-cooler 23 (not shown).
30 is the liquid hydrogen pipe connecting the inlet side of the pre-cooler 2.
31 is a low temperature hydrogen gas pipe connecting the outlet side of 3 and the inlet side of the high temperature hydrogen gas generator z7; 31 is the high temperature hydrogen gas generator 27;
33 is air and 34 is combustion gas.
空気取入れ口２２からエアターボラムジェット本体２１
内部に吸入された空気３３はブリクーラ２３を通って冷
却され、コンプレッサ２４で圧縮された後、燃焼室２６
へ送られる。From the air intake port 22 to the air turbo ramjet body 21
The air 33 taken into the interior is cooled through the pre-cooler 23, compressed by the compressor 24, and then transferred to the combustion chamber 26.
sent to.
一方、図示しない液体水素タンクからの高圧の液体水素
は、液体水素配管２９を通ってブリクーラ２３へ送られ
、ブリクーラ２３で前記したように空気３３を冷却する
ことにより熱交換されて気化し、次に、低温水素ガス配
管３０を通って高温水素ガス発生装置２７へ送られ、高
温水素ガス発生装置２７で燃焼ガス３４によって高温に
加熱され、その後、高温水素ガス配管３１を通ってター
ビン入口マニホールド３２からタービン２５へ送られ、
該タービン２５を駆動することにより図示しない駆動力
伝達機構によって接続されたコンプレッサ２４を駆動し
、燃焼室２６へ送られる。On the other hand, high-pressure liquid hydrogen from a liquid hydrogen tank (not shown) is sent to the pre-cooler 23 through the liquid hydrogen pipe 29, where it cools the air 33 as described above, undergoes heat exchange, and is vaporized. Then, it is sent to the high-temperature hydrogen gas generator 27 through the low-temperature hydrogen gas piping 30, heated to a high temperature by the combustion gas 34 in the high-temperature hydrogen gas generator 27, and then passed through the high-temperature hydrogen gas piping 31 to the turbine inlet manifold 32. is sent to the turbine 25 from
By driving the turbine 25, the compressor 24 connected to it by a driving force transmission mechanism (not shown) is driven, and the gas is sent to the combustion chamber 26.
こうして燃焼室２６へ送られた高温高圧の水素ガスは空
気３３により燃焼され、発生した燃焼ガス３４がノズル
２８から噴射されることによって推力を得るようになっ
ている。The high-temperature, high-pressure hydrogen gas thus sent to the combustion chamber 26 is combusted by the air 33, and the generated combustion gas 34 is injected from the nozzle 28 to obtain thrust.
［発明が解決しようとする課題］
しかしながら、上記従来の水素燃料用エンジンには、以
下のような問題があった。[Problems to be Solved by the Invention] However, the conventional hydrogen fuel engine described above has the following problems.
即ち、水素ガスは、常温において金属表面に吸着されて
金属の延性や強度の低下等のいわゆる水素ぜい化を引起
こす性質があり、又、水素ガスが金属中に侵入する量は
水素ガスが高温高圧である程多くなるという性質がある
ので、高温高圧の水素ガスにさらされる金属は内部まで
水素ぜい化されてしまうことになるが、上記した水素燃
料用エンジンでは、高温水素ガス発生装置６，７．２７
から高温水素ガス配管２０，３１、タービン１８，１９
，２５、燃焼室２．２６までの部材が高温高圧の水素ガ
スにさらされるので、これらの部材に水素ぜい化が起こ
る可能性がきわめて高い。In other words, hydrogen gas has the property of being adsorbed on the metal surface at room temperature and causing so-called hydrogen embrittlement, such as a decrease in the ductility and strength of the metal. Since hydrogen gas increases as the temperature and pressure increase, metals exposed to high-temperature, high-pressure hydrogen gas will become embrittled with hydrogen. 6,7.27
From high temperature hydrogen gas pipes 20, 31, turbines 18, 19
, 25, Since the members up to the combustion chamber 2.26 are exposed to high temperature and high pressure hydrogen gas, there is a very high possibility that hydrogen embrittlement will occur in these members.
一方、従来、水素ぜい化を防止する手段としては、金属
の表面に水素ぜい化に対して強い金メツキを施すことが
行われていたが、金は高価であり、水素ぜい化を防止で
きる程度の均−且つ緻密な被膜を金属の表面に形成する
ことが困難であり、しかも、高温に弱いという問題があ
り、水素燃料用エンジンに適用することが難しかった。On the other hand, conventional methods for preventing hydrogen embrittlement have been to apply gold plating to the metal surface, which is resistant to hydrogen embrittlement, but gold is expensive and It is difficult to form a uniform and dense film on the surface of a metal that can prevent this problem, and it is also susceptible to high temperatures, making it difficult to apply it to hydrogen fuel engines.
本発明は、上述の実情に鑑み、高温高圧の水素ガスによ
る水素ぜい化を防止し得るようにした水素燃料用エンジ
ンを提供することを目的とするものである。In view of the above-mentioned circumstances, it is an object of the present invention to provide a hydrogen-fueled engine that can prevent hydrogen embrittlement due to high-temperature, high-pressure hydrogen gas.
［課題を解決するための手段］
本発明は、液体水素を高温水素ガス発生装置で高温高圧
の水素ガスとした後に高温水素ガス配管、タービンを介
して燃焼室へ送り燃焼させるようにした水素燃料用エン
ジンにおいて、高温水素ガス発生装置から高温水素ガス
配管、タービン、燃焼室までの部材のうち少なくともタ
ービンプレードの金属母材表面にセラミックス系の水素
透過防止層を形成したことを特徴とする水素燃料用エン
ジンにかかるものである。[Means for Solving the Problems] The present invention provides a hydrogen fuel in which liquid hydrogen is converted into high-temperature, high-pressure hydrogen gas using a high-temperature hydrogen gas generator, and then sent to a combustion chamber via a high-temperature hydrogen gas pipe and a turbine for combustion. A hydrogen fuel for use in an engine, characterized in that a ceramic-based hydrogen permeation prevention layer is formed on the surface of at least the metal base material of the turbine blade among the members from the high-temperature hydrogen gas generator to the high-temperature hydrogen gas piping, the turbine, and the combustion chamber. This applies to the engine used.
［作 用］
本発明によれば、高温水素ガス発生装置から高温水素ガ
ス配管、タービン、燃焼室までの部材のうち少なくとも
タービンプレードの金属母材表面に形成されたセラミッ
クス系の水素透過防止層により、金属母材か水素ぜい化
を起こすことが防止される。[Function] According to the present invention, the ceramic hydrogen permeation prevention layer formed on the surface of the metal base material of at least the turbine blade among the members from the high-temperature hydrogen gas generator to the high-temperature hydrogen gas piping, the turbine, and the combustion chamber , hydrogen embrittlement of the metal base material is prevented.
［実 施 例］ 以下、本発明の実施例を図面を参照しつつ説明する。[Example] Embodiments of the present invention will be described below with reference to the drawings.
第１図・第゛２図は、本発明の一実施例である。FIGS. 1 and 2 show an embodiment of the present invention.
又、液体ロケットエンジンの構造については第３図を、
エアターボラムジェットの構造については第４図を参照
する。Also, regarding the structure of a liquid rocket engine, see Figure 3.
Refer to FIG. 4 for the structure of the air turboramjet.
第３図の液体ロケットエンジンでは高温水素ガス発生装
置６．７から高温水素ガス配管２０、タービン１８，１
９、燃焼室２までの高温水素ガスにさらされる部材、及
び、第４図のエアターボラムジェットでは高温水素ガス
発生装置２７から高温水素ガス配管３１、タービン２５
、燃焼室２６までの高温水素ガスにさらされる部材を構
成している、金属母材３５表面に、ニッケル、クロム、
アルミニウム、イツトリウム等の混合物等からなる数百
ミクロン程度の層厚の結合層３６を溶射等により形成し
、該結合層３６の表面にジルコニア等からなる数百ミク
ロン程度の層厚の遮熱層３７を溶射等により形成し、遮
熱層３７の表面にアルミナ（Ａｌ！０１）や酸化チタン
（Ｔｉｅｓ）等のセラミックス系の数ミクロン程度の層
厚の水素透過防止層３８をスパッタリング等により形成
する。In the liquid rocket engine shown in FIG.
9. Members exposed to high-temperature hydrogen gas up to the combustion chamber 2, and in the air turbo ramjet shown in FIG.
, nickel, chromium,
A bonding layer 36 made of a mixture of aluminum, yttrium, etc. and having a thickness of about several hundred microns is formed by thermal spraying or the like, and a heat shielding layer 37 made of zirconia or the like and having a thickness of about several hundred microns is formed on the surface of the bonding layer 36. A hydrogen permeation prevention layer 38 made of ceramics such as alumina (Al!01) or titanium oxide (Ties) and having a thickness of several microns is formed on the surface of the heat shield layer 37 by sputtering or the like.
第２図は上記構造を具体的にタービン１８，１９゜２５
のタービンプレード３９に適用した例である。Figure 2 shows the above structure specifically for turbines 18, 19°25.
This is an example in which the present invention is applied to a turbine blade 39.
尚、図中４０はブレード本体、４１はブレード基部、４
２はブレード取付は部である。In addition, in the figure, 40 is the blade body, 41 is the blade base, 4
2 is the blade attachment section.
尚、水素透過防止層３８は金属母材３５と結合層３６の
間に形成されることもある。Note that the hydrogen permeation prevention layer 38 may be formed between the metal base material 35 and the bonding layer 36.
次に、作動について説明する。Next, the operation will be explained.
液体ロケットエンジン及びエアターボラムジェットが推
力を発生する過程については第３図・第４図と同様なの
で説明を省略する。The process by which the liquid rocket engine and the air turbo ramjet generate thrust is the same as that shown in FIGS. 3 and 4, so a description thereof will be omitted.
液体ロケットエンジンの高温水素ガス発生装置６，７か
ら高温水素ガス配管２０、タービン１８，１９、燃焼室
２までの高温水素ガスにさらされる部材、及び、エアタ
ーボラムジェットの高温水素ガス発生装置２７から高温
水素ガス配管３１、タービン２５、燃焼室２６までの高
温水素ガスにさらされる部材を構成している、金属母材
３５表面の最外層に、アルミナや酸化チタン系等のセラ
ミックス系の数ミクロン程度の層厚の水素透過防止層３
８を設けたので、高温高圧の水素ガスが水素透過防止層
３８を透過して金属母材３５へ達するのが防止され、従
って、金属母材３５が水素ぜい化するのが防止される。Members exposed to high-temperature hydrogen gas from the high-temperature hydrogen gas generators 6 and 7 of the liquid rocket engine to the high-temperature hydrogen gas piping 20, the turbines 18 and 19, and the combustion chamber 2, and the high-temperature hydrogen gas generator 27 of the air turbo ramjet. The outermost layer of the surface of the metal base material 35, which constitutes the components exposed to high-temperature hydrogen gas from the high-temperature hydrogen gas piping 31 to the turbine 25 to the combustion chamber 26, is coated with several micrometers of ceramic-based material such as alumina or titanium oxide. Hydrogen permeation prevention layer 3 with a layer thickness of
8 prevents high-temperature, high-pressure hydrogen gas from passing through the hydrogen permeation prevention layer 38 and reaching the metal base material 35, thereby preventing hydrogen embrittlement of the metal base material 35.
又、水素透過防止層３８の内層としてジルコニア等から
なる数百ミクロン程度の層厚の遮熱層３７を設けたので
、高温高圧の水素ガスの熱が遮熱層３７で遮断され、金
属母材３５が高温化するのが防止される。この際、遮熱
層３７と金属母材３５の間にニッケル、クロム、アルミ
ニウム、イツトリウム等の混合物等からなる数百ミクロ
ン程度の層厚の結合層３６を設けたので、遮熱層３７と
金属母材３５との強固な結合状態が得られる。Moreover, since the heat shielding layer 37 made of zirconia or the like and having a thickness of several hundred microns is provided as the inner layer of the hydrogen permeation prevention layer 38, the heat of the high temperature and high pressure hydrogen gas is blocked by the heat shielding layer 37, and the metal base material 35 is prevented from increasing in temperature. At this time, a bonding layer 36 made of a mixture of nickel, chromium, aluminum, yttrium, etc. and having a thickness of about several hundred microns was provided between the heat shield layer 37 and the metal base material 35. A strong bond with the base material 35 can be obtained.
特に、苛酷な条件化に置かれたタービン１８゜１９．２
５のタービンプレード３９は最も高温高圧の水素ガスに
よる水素ぜい化を受けやすいので、少なくとも、タービ
ン１８，１９．２５のタービンプレード３９を上記構造
とすることにより、高温高圧の水素ガスによる水素ぜい
化の影響を全体として低減することができる。In particular, turbines 18°19.2 placed under harsh conditions
Since the turbine blades 39 of No. 5 are most susceptible to hydrogen embrittlement due to high-temperature, high-pressure hydrogen gas, at least the turbine blades 39 of turbines 18, 19. It is possible to reduce the impact of carbonization as a whole.
尚、本発明は、上述の実施例にのみ限定されるものでは
なく、水素燃料用エンジンは液体ロケットエンジンやエ
アターボラムジェットに限らないこと、その他、本発明
の要旨を逸脱しない範囲内において種々変更を加え得る
ことは勿論である。The present invention is not limited to the above-described embodiments, and the hydrogen fuel engine is not limited to a liquid rocket engine or an air turbo ramjet, and various other modifications may be made without departing from the gist of the present invention. Of course, modifications can be made.
し発明の効果］
以上説明したように、本発明の水素燃料用エンジンによ
れば、高温高圧の水素ガスによる水素ぜい化を防止する
ことができるという優れた効果を奏し得る。[Effects of the Invention] As described above, the hydrogen fuel engine of the present invention has the excellent effect of being able to prevent hydrogen embrittlement due to high-temperature, high-pressure hydrogen gas.
第１図は本発明の実施例の断面図、第２図は第１図の構
造を適用したタービンプレードの先端部を破断した斜視
図、第３図は液体ロケットエンジンの全体系統図、第４
図はエアターボラムジェットの概略側断面図である。
図中１は水素燃料用エンジンとしての液体ロケットエン
ジン本体、２．２６は燃焼室、６，７．２７は高温水素
ガス発生装置、ＩＣｌ３．２５はタービン、２０．３１
は高温水素ガス配管、２１は水素燃料用エンジンとして
のエアターボラムジェット本体、３５は金属母材、３８
は水素透過防止層、３９はタービンプレードを示す。
第１図
第３図
第２図Fig. 1 is a cross-sectional view of an embodiment of the present invention, Fig. 2 is a perspective view of the distal end of a turbine blade to which the structure of Fig. 1 is applied, Fig. 3 is an overall system diagram of a liquid rocket engine, and Fig. 4 is a cross-sectional view of an embodiment of the present invention.
The figure is a schematic side sectional view of an air turbo ramjet. In the figure, 1 is the main body of a liquid rocket engine as a hydrogen fuel engine, 2.26 is a combustion chamber, 6, 7.27 is a high-temperature hydrogen gas generator, ICl3.25 is a turbine, 20.31
21 is an air turbo ramjet body as a hydrogen fuel engine; 35 is a metal base material; 38 is a high-temperature hydrogen gas pipe;
3 represents a hydrogen permeation prevention layer, and 39 represents a turbine blade. Figure 1 Figure 3 Figure 2
Claims (1)
ガスとした後に高温水素ガス配管、タービンを介して燃
焼室へ送り燃焼させるようにした水素燃料用エンジンに
おいて、高温水素ガス発生装置から高温水素ガス配管、
タービン、燃焼室までの部材のうち少なくともタービン
プレードの金属母材表面にセラミックス系の水素透過防
止層を形成したことを特徴とする水素燃料用エンジン。1) In a hydrogen-fueled engine in which liquid hydrogen is converted into high-temperature, high-pressure hydrogen gas using a high-temperature hydrogen gas generator and then sent to a combustion chamber via high-temperature hydrogen gas piping and a turbine for combustion, high-temperature hydrogen gas is generated from the high-temperature hydrogen gas generator. hydrogen gas piping,
A hydrogen fuel engine characterized in that a ceramic hydrogen permeation prevention layer is formed on the surface of a metal base material of at least a turbine blade among the members up to the turbine and the combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP33677490A JPH04203465A (en) | 1990-11-30 | 1990-11-30 | Engine using hydrogen fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP33677490A JPH04203465A (en) | 1990-11-30 | 1990-11-30 | Engine using hydrogen fuel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04203465A true JPH04203465A (en) | 1992-07-24 |
Family
ID=18302573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP33677490A Pending JPH04203465A (en) | 1990-11-30 | 1990-11-30 | Engine using hydrogen fuel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04203465A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2746384A1 (en) * | 1996-03-19 | 1997-09-26 | K Bjuro Khimavtomatiki | METHOD OF PROTECTION AGAINST DESTRUCTION OF ENERGY PRODUCTION EQUIPMENT |
| CN109321866A (en) * | 2018-12-12 | 2019-02-12 | 中国航空制造技术研究院 | A kind of preparation method of titanium alloy gradient-structure |
| CN114592925A (en) * | 2022-03-31 | 2022-06-07 | 北京大臻科技有限公司 | Magnetic suspension hydrogen turbine expansion device and method |
-
1990
- 1990-11-30 JP JP33677490A patent/JPH04203465A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2746384A1 (en) * | 1996-03-19 | 1997-09-26 | K Bjuro Khimavtomatiki | METHOD OF PROTECTION AGAINST DESTRUCTION OF ENERGY PRODUCTION EQUIPMENT |
| US6156269A (en) * | 1996-03-19 | 2000-12-05 | Konstrutorskoe Bjuro Khimavtomatiki | Method of protecting high-energy machinery from corrosion damage |
| CN109321866A (en) * | 2018-12-12 | 2019-02-12 | 中国航空制造技术研究院 | A kind of preparation method of titanium alloy gradient-structure |
| CN109321866B (en) * | 2018-12-12 | 2021-10-29 | 中国航空制造技术研究院 | Preparation method of titanium alloy gradient structure |
| CN114592925A (en) * | 2022-03-31 | 2022-06-07 | 北京大臻科技有限公司 | Magnetic suspension hydrogen turbine expansion device and method |
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