Is presssuized gas absent in a turbopump-driven rocket engines?
$begingroup$
For RL-10 rocket engines, are the propellent pumps able to provide the propellent without a source of pressurant gas?
rockets propulsion engines combustion combustion-chamber
asked yesterday
user28833user28833
463
$endgroup$
add a comment |
$begingroup$
For RL-10 rocket engines, are the propellent pumps able to provide the propellent without a source of pressurant gas?
rockets propulsion engines combustion combustion-chamber
asked yesterday
user28833user28833
463
$endgroup$
add a comment |
$begingroup$
For RL-10 rocket engines, are the propellent pumps able to provide the propellent without a source of pressurant gas?
rockets propulsion engines combustion combustion-chamber
asked yesterday
user28833user28833
463
$endgroup$
For RL-10 rocket engines, are the propellent pumps able to provide the propellent without a source of pressurant gas?
rockets propulsion engines combustion combustion-chamber
rockets propulsion engines combustion combustion-chamber
asked yesterday
user28833user28833
463
asked yesterday
user28833user28833
463
edited yesterday
user28833
asked yesterday
user28833user28833
463
asked yesterday
user28833user28833
463
asked yesterday
user28833user28833
463
463
add a comment |
add a comment |
2 Answers
2
active
oldest
votes
$begingroup$
The ACES upper stage (in development at the moment) is being designed to do without an external source of pressurizing gas:
Fundamentally IVF is a Hydrogen/Oxygen auxiliary power unit, that uses free boiloff hydrogen and oxygen to generate electricity (eliminating main vehicle batteries), provide autogenous tank pressurization (eliminating most or all Helium bottles), and feed GH2/GO2 reaction control system thrusters (eliminating all stored hydrazine).
The system uses the heat from the IVF internal combustion engine to heat up the propellant for tank pressurization:
This heat rejection feature is much desired in the IVF engine since we wish to scavenge heat for tank pressurization
IOW the IVF boils some of the hydrogen/oxygen and uses the resulting gas to pressurize the tanks.
answered yesterday
HobbesHobbes
89.9k2254405
$endgroup$
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
add a comment |
$begingroup$
No, the Centaur with its RL-10 engines requires tank pressurization.
Helium Supply and Pressurization System - Helium is the main
pressurant used for tank pressurization. Typically, four 26-inch
diameter high-pressure helium bottles mounted on the aft bulkhead are
used for storage. They are made of a graphite/epoxy composite overwrap
enveloping a stainless steel or aluminum liner. These bottles are
charged to 4000 psia prior to liftoff. Helium in-flight purges are
used for the sense lines, LO2 vent valve and the LO2 bubbler line.
The
bottles are manifold together and are linked to two pressurization
valve modules, one for each propellant tank. Each valve module
contains four individual valves, which provide single failure
tolerance both to open or close. Helium is used for tank
pressurization prior to engine burns. A hydrogen autogenous system
bleeds gaseous hydrogen off the engines and is used for LH2
pressurization during the engine burns. A valve module identical to
those used for helium pressurization provides control.
Source
Image Source
See also How does tank pressurization work? and Disposition of the Oxidizer Tank in Rockets with Autogenous Pressurization
answered yesterday
Organic MarbleOrganic Marble
56k3150239
$endgroup$
add a comment |
Your Answer
StackExchange.ifUsing("editor", function () {
return StackExchange.using("mathjaxEditing", function () {
StackExchange.MarkdownEditor.creationCallbacks.add(function (editor, postfix) {
StackExchange.mathjaxEditing.prepareWmdForMathJax(editor, postfix, [["$", "$"], ["\\(","\\)"]]);
});
});
}, "mathjax-editing");
StackExchange.ready(function() {
var channelOptions = {
tags: "".split(" "),
id: "508"
};
initTagRenderer("".split(" "), "".split(" "), channelOptions);
StackExchange.using("externalEditor", function() {
// Have to fire editor after snippets, if snippets enabled
if (StackExchange.settings.snippets.snippetsEnabled) {
StackExchange.using("snippets", function() {
createEditor();
});
}
else {
createEditor();
}
});
function createEditor() {
StackExchange.prepareEditor({
heartbeatType: 'answer',
autoActivateHeartbeat: false,
convertImagesToLinks: false,
noModals: true,
showLowRepImageUploadWarning: true,
reputationToPostImages: null,
bindNavPrevention: true,
postfix: "",
imageUploader: {
brandingHtml: "Powered by u003ca class="icon-imgur-white" href="https://imgur.com/"u003eu003c/au003e",
contentPolicyHtml: "User contributions licensed under u003ca href="https://creativecommons.org/licenses/by-sa/3.0/"u003ecc by-sa 3.0 with attribution requiredu003c/au003e u003ca href="https://stackoverflow.com/legal/content-policy"u003e(content policy)u003c/au003e",
allowUrls: true
},
noCode: true, onDemand: true,
discardSelector: ".discard-answer"
,immediatelyShowMarkdownHelp:true
});
}
});
Sign up or log in
StackExchange.ready(function () {
StackExchange.helpers.onClickDraftSave('#login-link');
});
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Post as a guest
Required, but never shown
StackExchange.ready(
function () {
StackExchange.openid.initPostLogin('.new-post-login', 'https%3a%2f%2fspace.stackexchange.com%2fquestions%2f33983%2fis-presssuized-gas-absent-in-a-turbopump-driven-rocket-engines%23new-answer', 'question_page');
}
);
Post as a guest
Required, but never shown
2 Answers
2
active
oldest
votes
2 Answers
2
active
oldest
votes
active
oldest
votes
active
oldest
votes
$begingroup$
The ACES upper stage (in development at the moment) is being designed to do without an external source of pressurizing gas:
Fundamentally IVF is a Hydrogen/Oxygen auxiliary power unit, that uses free boiloff hydrogen and oxygen to generate electricity (eliminating main vehicle batteries), provide autogenous tank pressurization (eliminating most or all Helium bottles), and feed GH2/GO2 reaction control system thrusters (eliminating all stored hydrazine).
The system uses the heat from the IVF internal combustion engine to heat up the propellant for tank pressurization:
This heat rejection feature is much desired in the IVF engine since we wish to scavenge heat for tank pressurization
IOW the IVF boils some of the hydrogen/oxygen and uses the resulting gas to pressurize the tanks.
answered yesterday
HobbesHobbes
89.9k2254405
$endgroup$
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
add a comment |
$begingroup$
The ACES upper stage (in development at the moment) is being designed to do without an external source of pressurizing gas:
Fundamentally IVF is a Hydrogen/Oxygen auxiliary power unit, that uses free boiloff hydrogen and oxygen to generate electricity (eliminating main vehicle batteries), provide autogenous tank pressurization (eliminating most or all Helium bottles), and feed GH2/GO2 reaction control system thrusters (eliminating all stored hydrazine).
The system uses the heat from the IVF internal combustion engine to heat up the propellant for tank pressurization:
This heat rejection feature is much desired in the IVF engine since we wish to scavenge heat for tank pressurization
IOW the IVF boils some of the hydrogen/oxygen and uses the resulting gas to pressurize the tanks.
answered yesterday
HobbesHobbes
89.9k2254405
$endgroup$
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
add a comment |
$begingroup$
The ACES upper stage (in development at the moment) is being designed to do without an external source of pressurizing gas:
Fundamentally IVF is a Hydrogen/Oxygen auxiliary power unit, that uses free boiloff hydrogen and oxygen to generate electricity (eliminating main vehicle batteries), provide autogenous tank pressurization (eliminating most or all Helium bottles), and feed GH2/GO2 reaction control system thrusters (eliminating all stored hydrazine).
The system uses the heat from the IVF internal combustion engine to heat up the propellant for tank pressurization:
This heat rejection feature is much desired in the IVF engine since we wish to scavenge heat for tank pressurization
IOW the IVF boils some of the hydrogen/oxygen and uses the resulting gas to pressurize the tanks.
answered yesterday
HobbesHobbes
89.9k2254405
$endgroup$
The ACES upper stage (in development at the moment) is being designed to do without an external source of pressurizing gas:
Fundamentally IVF is a Hydrogen/Oxygen auxiliary power unit, that uses free boiloff hydrogen and oxygen to generate electricity (eliminating main vehicle batteries), provide autogenous tank pressurization (eliminating most or all Helium bottles), and feed GH2/GO2 reaction control system thrusters (eliminating all stored hydrazine).
The system uses the heat from the IVF internal combustion engine to heat up the propellant for tank pressurization:
This heat rejection feature is much desired in the IVF engine since we wish to scavenge heat for tank pressurization
IOW the IVF boils some of the hydrogen/oxygen and uses the resulting gas to pressurize the tanks.
answered yesterday
HobbesHobbes
89.9k2254405
edited yesterday
answered yesterday
HobbesHobbes
89.9k2254405
answered yesterday
HobbesHobbes
89.9k2254405
answered yesterday
HobbesHobbes
89.9k2254405
89.9k2254405
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
add a comment |
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
$begingroup$
ah, yes. I'll clarify.
$endgroup$
– Hobbes
yesterday
add a comment |
$begingroup$
No, the Centaur with its RL-10 engines requires tank pressurization.
Helium Supply and Pressurization System - Helium is the main
pressurant used for tank pressurization. Typically, four 26-inch
diameter high-pressure helium bottles mounted on the aft bulkhead are
used for storage. They are made of a graphite/epoxy composite overwrap
enveloping a stainless steel or aluminum liner. These bottles are
charged to 4000 psia prior to liftoff. Helium in-flight purges are
used for the sense lines, LO2 vent valve and the LO2 bubbler line.
The
bottles are manifold together and are linked to two pressurization
valve modules, one for each propellant tank. Each valve module
contains four individual valves, which provide single failure
tolerance both to open or close. Helium is used for tank
pressurization prior to engine burns. A hydrogen autogenous system
bleeds gaseous hydrogen off the engines and is used for LH2
pressurization during the engine burns. A valve module identical to
those used for helium pressurization provides control.
Source
Image Source
See also How does tank pressurization work? and Disposition of the Oxidizer Tank in Rockets with Autogenous Pressurization
answered yesterday
Organic MarbleOrganic Marble
56k3150239
$endgroup$
add a comment |
$begingroup$
No, the Centaur with its RL-10 engines requires tank pressurization.
Helium Supply and Pressurization System - Helium is the main
pressurant used for tank pressurization. Typically, four 26-inch
diameter high-pressure helium bottles mounted on the aft bulkhead are
used for storage. They are made of a graphite/epoxy composite overwrap
enveloping a stainless steel or aluminum liner. These bottles are
charged to 4000 psia prior to liftoff. Helium in-flight purges are
used for the sense lines, LO2 vent valve and the LO2 bubbler line.
The
bottles are manifold together and are linked to two pressurization
valve modules, one for each propellant tank. Each valve module
contains four individual valves, which provide single failure
tolerance both to open or close. Helium is used for tank
pressurization prior to engine burns. A hydrogen autogenous system
bleeds gaseous hydrogen off the engines and is used for LH2
pressurization during the engine burns. A valve module identical to
those used for helium pressurization provides control.
Source
Image Source
See also How does tank pressurization work? and Disposition of the Oxidizer Tank in Rockets with Autogenous Pressurization
answered yesterday
Organic MarbleOrganic Marble
56k3150239
$endgroup$
add a comment |
$begingroup$
No, the Centaur with its RL-10 engines requires tank pressurization.
Helium Supply and Pressurization System - Helium is the main
pressurant used for tank pressurization. Typically, four 26-inch
diameter high-pressure helium bottles mounted on the aft bulkhead are
used for storage. They are made of a graphite/epoxy composite overwrap
enveloping a stainless steel or aluminum liner. These bottles are
charged to 4000 psia prior to liftoff. Helium in-flight purges are
used for the sense lines, LO2 vent valve and the LO2 bubbler line.
The
bottles are manifold together and are linked to two pressurization
valve modules, one for each propellant tank. Each valve module
contains four individual valves, which provide single failure
tolerance both to open or close. Helium is used for tank
pressurization prior to engine burns. A hydrogen autogenous system
bleeds gaseous hydrogen off the engines and is used for LH2
pressurization during the engine burns. A valve module identical to
those used for helium pressurization provides control.
Source
Image Source
See also How does tank pressurization work? and Disposition of the Oxidizer Tank in Rockets with Autogenous Pressurization
answered yesterday
Organic MarbleOrganic Marble
56k3150239
$endgroup$
No, the Centaur with its RL-10 engines requires tank pressurization.
Helium Supply and Pressurization System - Helium is the main
pressurant used for tank pressurization. Typically, four 26-inch
diameter high-pressure helium bottles mounted on the aft bulkhead are
used for storage. They are made of a graphite/epoxy composite overwrap
enveloping a stainless steel or aluminum liner. These bottles are
charged to 4000 psia prior to liftoff. Helium in-flight purges are
used for the sense lines, LO2 vent valve and the LO2 bubbler line.
The
bottles are manifold together and are linked to two pressurization
valve modules, one for each propellant tank. Each valve module
contains four individual valves, which provide single failure
tolerance both to open or close. Helium is used for tank
pressurization prior to engine burns. A hydrogen autogenous system
bleeds gaseous hydrogen off the engines and is used for LH2
pressurization during the engine burns. A valve module identical to
those used for helium pressurization provides control.
Source
Image Source
See also How does tank pressurization work? and Disposition of the Oxidizer Tank in Rockets with Autogenous Pressurization
answered yesterday
Organic MarbleOrganic Marble
56k3150239
edited yesterday
answered yesterday
Organic MarbleOrganic Marble
56k3150239
answered yesterday
Organic MarbleOrganic Marble
56k3150239
answered yesterday
Organic MarbleOrganic Marble
56k3150239
56k3150239
add a comment |
add a comment |
Thanks for contributing an answer to Space Exploration Stack Exchange!
- Please be sure to answer the question. Provide details and share your research!
But avoid …
- Asking for help, clarification, or responding to other answers.
- Making statements based on opinion; back them up with references or personal experience.
Use MathJax to format equations. MathJax reference.
To learn more, see our tips on writing great answers.
Sign up or log in
StackExchange.ready(function () {
StackExchange.helpers.onClickDraftSave('#login-link');
});
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Post as a guest
Required, but never shown
StackExchange.ready(
function () {
StackExchange.openid.initPostLogin('.new-post-login', 'https%3a%2f%2fspace.stackexchange.com%2fquestions%2f33983%2fis-presssuized-gas-absent-in-a-turbopump-driven-rocket-engines%23new-answer', 'question_page');
}
);
Post as a guest
Required, but never shown
Sign up or log in
StackExchange.ready(function () {
StackExchange.helpers.onClickDraftSave('#login-link');
});
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Post as a guest
Required, but never shown
Sign up or log in
StackExchange.ready(function () {
StackExchange.helpers.onClickDraftSave('#login-link');
});
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Post as a guest
Required, but never shown
Sign up or log in
StackExchange.ready(function () {
StackExchange.helpers.onClickDraftSave('#login-link');
});
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Sign up using Google
Sign up using Facebook
Sign up using Email and Password
Post as a guest
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
Required, but never shown
