US710130A - Regenerator-burner. - Google Patents

Regenerator-burner. Download PDF

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Publication number
US710130A
US710130A US71609999A US1899716099A US710130A US 710130 A US710130 A US 710130A US 71609999 A US71609999 A US 71609999A US 1899716099 A US1899716099 A US 1899716099A US 710130 A US710130 A US 710130A
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air
burner
chamber
nozzle
combustion
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US71609999A
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Carl W Weiss
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44Feeding propellants
    • F02K9/50Feeding propellants using pressurised fluid to pressurise the propellants

Definitions

  • This invention relates to that form of prime mover or source of energy in which the pressure depends upon the development of high temperature usually produced by continuous combustion, the energy being utilized by direct impingement of the hot blast upon a moving body, such as the blades or buckets,
  • the object of the invention is to produce an improved device of the character referred to which shall have the highest possible efficiency without complication of construction,
  • the combustible is preferably formed by the admixture ofV av suitable fuel in the form of oil or otherwise and air or other suitable gas under conditions which permit of perfect con! trol, both as to the quality of the combusti# ble .and the pressure under which it is delivered, and air or other supporter of combustion is supplied undera less pressure to the' A' burner-chamber and so also that the waste of heat by radiation from the burner-chamber and otherwise is reduced to aminimum.
  • Fig. 3 is a partial view ⁇ illustrating a modification of the burner for using coaldust as fuel.
  • the burner-chamber is formed by a wall A, preferably of metal, which has referabl 'a lining B, of some refractor material, for contact with the llame.
  • 'lhefouter surface of the wall A may be corrugated, as at a, for a purpose presently to be referred to, and a jacket A surrounds the whole,
  • the air or other supporter of combustion may be supplied from any suitable source, such as a compressed-air reservoir,
  • the combustible is formed by an adrnixture of hydrocarbon and air, the latter being supplied, it may be, from the reservoir C.
  • An oil receptacle or carbureter D is interposed between the source of air and the point of combustion,the air-delivery pipe c being here shown as connected to the top of such vessel.
  • One pipe d extends from the top of such vessel to the air-nozzle e of the burner E, and a second piped', having a regulating stop-cock ⁇ d, extends from a point near the bottom of such vessel to the chamber e', surrounding the' nozzle e and communicating withV the burner-nozzle e2.
  • the aspirating action of the current of air which issues from the nozzle e draws the oil from the chamber e and Vaporizes it, thereby forming a combustible mixture which is ignitedat the burner-nozzle e2.
  • An adjustable needle-valve 'E' regulates the passage of air through the nozzle e.
  • the action of the ICO burner-nozzle e2 can be regulated and determined and that through the action of the regulator C2 the pressure ou the air or other supporter of combustion as it is delivered to the burner-chamber can be further regulated so that it shall be less than the pressure on the combustible.
  • the air or othersupporter of combustion passes from the inlet 1,2 to the distributinginlets a3 in a general direction opposite to the movement of the products of combustion within the burner and is itself heated to a high temperature by contact. with the corrugated Wall of the burner-cham ber and carries with it the heat which would be lost by radiation from the wall of the burner-chamber or otherwise.
  • the wall of the burner-chamber is represented as having a removable plug F, which can be withdrawn to permit the introduction of a primary igniter, or it may itself carry the electrodesf of an ordinary electric igniter.
  • the nozzle G of lava or nickel alloy or other suitable material, is insulated from the wall of the burner or combustion chamber by asbestosinsulation,as at g,orin anyothersuitable manner, so that the reduction of the temperature of the nozzle by conduction shallbe as little as possible. Furthermore, the bore g of the nozzle is enlarged outwardly, so that the products of combustion are expanded and delivered to the motorat the highest possible velocity. It will be observed that the nozzle E is also insulated from the body of the burner-chamber so as to prevent loss of heat and also to prevent overheating and consequent decomposition of the oil in its passage to the point of ignition.
  • the delivery-nozzle G is a blastnozzle and delivers the products of combustion directly from the burner-chamber to the motor, so that the jet or blast acts directly by impact upon the blades or paddles of the motor.
  • the proximity of the motor and the burner-chamber is important for the reason that it secures the delivery to the motor of the products of combustion at a maximum temperature,the efticiency of the motor being determined by the difference between the temperature where the blast strikes the in otor and that oi' the ejrhaust.
  • the motor it is to be observed, is driven by the impact of the products of combustion, not by using such products eXpansively.
  • nozzle G is shown as connected directly with a port h in the casing H of a motor-wheel I, the blast from the nozzle being directed against the paddles or buckets of such wheel.
  • the air on its way from the reservoir C to the burnerchamber to support combustion therein is conducted by means of pipes c2 to a chamber I-I', surrounding the wheel I and formed in the casing H, where it is heated by the eX- haust from the ports h.
  • the air may be compressed into a reservoir C by means of a pump K, operated from the shaft Il of the motor I through the gears t' and 7c.
  • FIG. 3 is illustrated a construction adapted for the use of coal-dust as fuel.
  • a suitable receptacle L is provided for the reception of the coal dust and communicates with the chamber e in rear of the burner-nozzle e2 through a passage in which is placed a feeding device, such as the worm L'.
  • the air under pressure from the reservoir C, controlled by the regulating device C', is delivered to the chamber c' and nozzle e2 through a nozzle e.
  • the blast of air drives the fuel with it through the burner-nozzle, Where it is ignited and burns, as already described.
  • a regenerator burner comprising a closed burner-chamber having an outlet-nozzle at one end, and air-inlets at its other end, means for supplying air to said inlets to support combustion, an injector also at said lastnamed end, an oil-reservoir, a pipe leading from below the oil-level up to one member of the injector, a second pipe leading from above the oil-level in said chamber t-o the other member of the injector, and a compressed-air pipe discharging air into the upper end of the oilreceptacle to force oil through one pipe and carbureted air through the other; substantially as described.
  • a regenerator burner comprising a closed air-jacketed burner-chamber, having air-inlets at one end from said jacket and provided at its opposite end with a discharge-nozzle, an injector at the air-inlet end of the chamber, an oil-reservoir, a pipe leading from below the oil-level of said reservoir to one member of the injector, a second pipe leading from above the oil-level to the other member of said injector; a compressed-air reservoir, and pipe leading from said air-reservoir to the air-jacket and upper part of the oil-reservoir and provided with pressure-regulating valves to cause the pressure at the air- IOO IIO
  • a rcgeneratorburner comprising the jacketed chamber A having a contracted outlet end, a lining fitting the chamber and also having a contracted outlet registering with that ofthe chamber, inlet-apertures from the jacketed space to the interior of the combustion-chamber, an annular plug screwed into the open end of the chamber and engaging that end of the lining to hold it in place, a blast-nozzle at the opposite end of the chamber, an air-nozzle screwed into said annular plug, an oil-nozzle screwed into the air-nozzle, an air and oil supply for said nozzle, and an air-supply for the chamber-jacket; substantially as described.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Description

Patented sept. so, |902.
2 Sheets-sheet l.
C. W. WEISS. REGENERATUR BRNEFL (Application filed May 8,' 13.99A);
QQ. I i a @M E, /A 0 \\f ///1?///// 4 No. 7|o,|3o.
(No Modell.)
8 1W IN1.
N0. 7|,|30. Patented Sept. 30, |902.
C. W. WEISS. A
REGENERAWRHBUMER.
(Application led May 9, 1899.)
(No Model.)
2 Sheets'-Sheet 2.
ma Noam: PETERS ucm-uws.. wAsmNuom n4 c l UNITED STATES PATENT EEtcE.
CARL W. WEISS, OF NEW YORK, N. Y.
REGENERATOR-BURNER.
SPECIFICATION forming part of Letters Patent No. 710,130, dated September 30, 1902.
Application led May 9. 1899. Serial No.
.To all whom/t may concern:
Beit known thatI, CARL W. WEIss, a citizen of the United States, residing in the borough ofManhattan, city of'New York, State of New York, have invented certain new and useful Improvements in Regenerator-Burners, of which the following is a specification,
reference being had to the accompanying drawings, forming a partfhereof.
This invention relates to that form of prime mover or source of energy in which the pressure depends upon the development of high temperature usually produced by continuous combustion, the energy being utilized by direct impingement of the hot blast upon a moving body, such as the blades or buckets,
of a turbine or other wheel.
The object of the invention is to produce an improved device of the character referred to which shall have the highest possible efficiency without complication of construction,
as more fully described hereinafter. The combustible is preferably formed by the admixture ofV av suitable fuel in the form of oil or otherwise and air or other suitable gas under conditions which permit of perfect con! trol, both as to the quality of the combusti# ble .and the pressure under which it is delivered, and air or other supporter of combustion is supplied undera less pressure to the' A' burner-chamber and so also that the waste of heat by radiation from the burner-chamber and otherwise is reduced to aminimum.
The invention will be fully explained hereinafter with reference to the accompanying drawings, in which'- t i Figure l is a View, partly in section and partly in elevation, of a burner which embodies the invention and of the adjuncts of such burner. -Fig. 2 is a similar View, but
on a smaller scale, illustrating the application of the invention to a turbine or other 716,099. (No model.)
wheel. Fig. 3 is a partial view `illustrating a modification of the burner for using coaldust as fuel.
In the construction shown in Figs. l and 2 Vof the drawings the burner-chamber is formed by a wall A, preferably of metal, which has referabl 'a lining B, of some refractor material, for contact with the llame. 'lhefouter surface of the wall A may be corrugated, as at a, for a purpose presently to be referred to, and a jacket A surrounds the whole,
leaving a space a', through which the incoming air or other supporterof combustion circulates in its passage from the inlet a2, near the remote end of the jacketed space, to, the holes a3, by whichit is admitted to thebu'rner chamber near the origin of combustion therein. The air or other supporter of combustion may be supplied from any suitable source, such as a compressed-air reservoir,
`(indicated at 0,) which is connected with the inlet d2 through a pressure-regulating device,
(represented at OQ) by which the escape of air from the reservoir is determined, and a second pressure-regulating deviceat Oby which the pressure at which the air or other supporter ofcombustion is supplied to the burnerchamber can be regulated. In this instance the combustible is formed by an adrnixture of hydrocarbon and air, the latter being supplied, it may be, from the reservoir C. An oil receptacle or carbureter D is interposed between the source of air and the point of combustion,the air-delivery pipe c being here shown as connected to the top of such vessel. One pipe d extends from the top of such vessel to the air-nozzle e of the burner E, and a second piped', having a regulating stop-cock` d, extends from a point near the bottom of such vessel to the chamber e', surrounding the' nozzle e and communicating withV the burner-nozzle e2. The aspirating action of the current of air which issues from the nozzle e draws the oil from the chamber e and Vaporizes it, thereby forming a combustible mixture which is ignitedat the burner-nozzle e2. An adjustable needle-valve 'E' regulates the passage of air through the nozzle e.
It will be observed that by the action of the ICO burner-nozzle e2 can be regulated and determined and that through the action of the regulator C2 the pressure ou the air or other supporter of combustion as it is delivered to the burner-chamber can be further regulated so that it shall be less than the pressure on the combustible. It will be further observed that the air or othersupporter of combustion passes from the inlet 1,2 to the distributinginlets a3 in a general direction opposite to the movement of the products of combustion within the burner and is itself heated to a high temperature by contact. with the corrugated Wall of the burner-cham ber and carries with it the heat which would be lost by radiation from the wall of the burner-chamber or otherwise.
In commencing the use of the device it is obviously necessary to employ a primary igniter of some sort, and for that purpose the wall of the burner-chamber is represented as having a removable plug F, which can be withdrawn to permit the introduction of a primary igniter, or it may itself carry the electrodesf of an ordinary electric igniter.
It will be understood that through the supply of air or other supporter of combustion the combustion within the burner-chamber is complete. The products of this combustion can escape from the closed burner-chamber only through the nozzle which is provided for the purpose, from which they pass to the motor. In the practical operation of hot-air turbines it is found that in the passage of the products of combustion through the necessarily small nozzles the loss ofheat is considerable because of the relatively large surface for contact with the products of combustion in proportion to the area of opening. In order to prevent this loss in the present case, the nozzle G, of lava or nickel alloy or other suitable material, is insulated from the wall of the burner or combustion chamber by asbestosinsulation,as at g,orin anyothersuitable manner, so that the reduction of the temperature of the nozzle by conduction shallbe as little as possible. Furthermore, the bore g of the nozzle is enlarged outwardly, so that the products of combustion are expanded and delivered to the motorat the highest possible velocity. It will be observed that the nozzle E is also insulated from the body of the burner-chamber so as to prevent loss of heat and also to prevent overheating and consequent decomposition of the oil in its passage to the point of ignition. It Will also be understood that the delivery-nozzle G is a blastnozzle and delivers the products of combustion directly from the burner-chamber to the motor, so that the jet or blast acts directly by impact upon the blades or paddles of the motor. The proximity of the motor and the burner-chamber is important for the reason that it secures the delivery to the motor of the products of combustion at a maximum temperature,the efticiency of the motor being determined by the difference between the temperature where the blast strikes the in otor and that oi' the ejrhaust. The motor, it is to be observed, is driven by the impact of the products of combustion, not by using such products eXpansively.
In Fig. 2 the nozzle G is shown as connected directly with a port h in the casing H of a motor-wheel I, the blast from the nozzle being directed against the paddles or buckets of such wheel. In this arrangement the air on its way from the reservoir C to the burnerchamber to support combustion therein is conducted by means of pipes c2 to a chamber I-I', surrounding the wheel I and formed in the casing H, where it is heated by the eX- haust from the ports h. The air may be compressed into a reservoir C by means of a pump K, operated from the shaft Il of the motor I through the gears t' and 7c.
In Fig. 3 is illustrated a construction adapted for the use of coal-dust as fuel. A suitable receptacle L is provided for the reception of the coal dust and communicates with the chamber e in rear of the burner-nozzle e2 through a passage in which is placed a feeding device, such as the worm L'. The air under pressure from the reservoir C, controlled by the regulating device C', is delivered to the chamber c' and nozzle e2 through a nozzle e. The blast of air drives the fuel with it through the burner-nozzle, Where it is ignited and burns, as already described.
It Will be understood that the invention is not to be limited to the precise construction and arrangement of parts shown and described herein, as the same may be varied without departing from the spirit of the invention.
I claim as my invention- 1. A regenerator burner, comprising a closed burner-chamber having an outlet-nozzle at one end, and air-inlets at its other end, means for supplying air to said inlets to support combustion, an injector also at said lastnamed end, an oil-reservoir, a pipe leading from below the oil-level up to one member of the injector, a second pipe leading from above the oil-level in said chamber t-o the other member of the injector, and a compressed-air pipe discharging air into the upper end of the oilreceptacle to force oil through one pipe and carbureted air through the other; substantially as described.
2. A regenerator burner comprising a closed air-jacketed burner-chamber, having air-inlets at one end from said jacket and provided at its opposite end with a discharge-nozzle, an injector at the air-inlet end of the chamber, an oil-reservoir, a pipe leading from below the oil-level of said reservoir to one member of the injector, a second pipe leading from above the oil-level to the other member of said injector; a compressed-air reservoir, and pipe leading from said air-reservoir to the air-jacket and upper part of the oil-reservoir and provided with pressure-regulating valves to cause the pressure at the air- IOO IIO
inlets of the burner-chamber to be less than the pressure at the injector; substantially as described. Y
3. The combination with an air-jacketed burner-chamber, having air-inlets from its jaeketed space, an injector for the chamber,v means for supplyingoil to the injector, a compressed-air reservoir, piping connecting the reservoir with the injector and oil-reservoir, and piping leading from the air-resem voir to the air-space around the burner-chainber, of an engine or motorhavingan air-jacket incorporated in the piping leading `to said burner-chamber, and' anozzle or pipe connecting the outlet end of the burner-chamber with the motor or engine; substantially as described.
4. The combination with the air-jacketed burner-chamber having air-inlets from its jacketed space, and an injector for combustible material, of a compressed-air reservoir,`
force at the injector than at the air-inlets of the burner-chamber; substantially as de-x scribed.
5. A rcgeneratorburner, comprising the jacketed chamber A having a contracted outlet end, a lining fitting the chamber and also having a contracted outlet registering with that ofthe chamber, inlet-apertures from the jacketed space to the interior of the combustion-chamber, an annular plug screwed into the open end of the chamber and engaging that end of the lining to hold it in place, a blast-nozzle at the opposite end of the chamber, an air-nozzle screwed into said annular plug, an oil-nozzle screwed into the air-nozzle, an air and oil supply for said nozzle, and an air-supply for the chamber-jacket; substantially as described.
This specification signed and witnessed this Sth day of May, A. D'. 1899.
CARL W. 'WEISS In presence of-I- W. B. GREELEY, L. R. MOORE.
US71609999A 1899-05-09 1899-05-09 Regenerator-burner. Expired - Lifetime US710130A (en)

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2500925A (en) * 1943-03-13 1950-03-21 Claude A Bonvillian Apparatus for the combustion of fuel
US2530271A (en) * 1946-06-18 1950-11-14 Swindin Norman Submerged flame burner
US2601000A (en) * 1947-05-23 1952-06-17 Gen Electric Combustor for thermal power plants having toroidal flow path in primary mixing zone
US2638895A (en) * 1946-08-19 1953-05-19 Swindin Norman Submerged flame burner
US2698050A (en) * 1949-06-10 1954-12-28 Lummus Co Combustion for liquid fuels
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2729060A (en) * 1951-07-07 1956-01-03 Armstrong Siddeley Motors Ltd Means for providing working fluid for a fluid-operable starter motor for a prime mover
US2773488A (en) * 1952-02-21 1956-12-11 Jet Heet Inc Boiler-burner unit
US2794319A (en) * 1953-03-02 1957-06-04 Westinghouse Electric Corp Afterburner shell construction
US2851854A (en) * 1955-01-21 1958-09-16 United Aircraft Corp Afterburner liner
US2962862A (en) * 1957-07-23 1960-12-06 David N Goldstein Double walled combustion chamber
US2986881A (en) * 1958-04-23 1961-06-06 United Aircraft Corp Fuel accumulator for aircraft jet engine starter
US3161228A (en) * 1961-05-17 1964-12-15 Brodlin Willi Method of gasifying liquid fuels
US3256688A (en) * 1961-11-24 1966-06-21 Charles C Hill Controlled combustion of solid propellants
US4466250A (en) * 1981-02-03 1984-08-21 Nissan Motor Company, Limited Air passageway to air injection valve for gas turbine engine
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
JP2004144469A (en) * 2002-10-24 2004-05-20 General Electric Co <Ge> Combustor liner with inverted turbulator
US20060219191A1 (en) * 2005-04-04 2006-10-05 United Technologies Corporation Heat transfer enhancement features for a tubular wall combustion chamber
US20070264602A1 (en) * 2006-01-26 2007-11-15 Frenette Henry E Vapor fuel combustion system
US20090071160A1 (en) * 2007-09-14 2009-03-19 Siemens Power Generation, Inc. Wavy CMC Wall Hybrid Ceramic Apparatus
US8307654B1 (en) * 2009-09-21 2012-11-13 Florida Turbine Technologies, Inc. Transition duct with spiral finned cooling passage
US9657938B2 (en) 2014-02-07 2017-05-23 Eugene R. Frenette Fuel combustion system
US9874349B2 (en) 2015-04-03 2018-01-23 Eugene R. Frenette Fuel combustion system
US20230332561A1 (en) * 2020-09-16 2023-10-19 Shanghai Institute Of Space Propulsion Cryogenic engine for space apparatus

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2500925A (en) * 1943-03-13 1950-03-21 Claude A Bonvillian Apparatus for the combustion of fuel
US2530271A (en) * 1946-06-18 1950-11-14 Swindin Norman Submerged flame burner
US2638895A (en) * 1946-08-19 1953-05-19 Swindin Norman Submerged flame burner
US2601000A (en) * 1947-05-23 1952-06-17 Gen Electric Combustor for thermal power plants having toroidal flow path in primary mixing zone
US2698050A (en) * 1949-06-10 1954-12-28 Lummus Co Combustion for liquid fuels
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2729060A (en) * 1951-07-07 1956-01-03 Armstrong Siddeley Motors Ltd Means for providing working fluid for a fluid-operable starter motor for a prime mover
US2773488A (en) * 1952-02-21 1956-12-11 Jet Heet Inc Boiler-burner unit
US2794319A (en) * 1953-03-02 1957-06-04 Westinghouse Electric Corp Afterburner shell construction
US2851854A (en) * 1955-01-21 1958-09-16 United Aircraft Corp Afterburner liner
US2962862A (en) * 1957-07-23 1960-12-06 David N Goldstein Double walled combustion chamber
US2986881A (en) * 1958-04-23 1961-06-06 United Aircraft Corp Fuel accumulator for aircraft jet engine starter
US3161228A (en) * 1961-05-17 1964-12-15 Brodlin Willi Method of gasifying liquid fuels
US3256688A (en) * 1961-11-24 1966-06-21 Charles C Hill Controlled combustion of solid propellants
US4466250A (en) * 1981-02-03 1984-08-21 Nissan Motor Company, Limited Air passageway to air injection valve for gas turbine engine
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
KR100825143B1 (en) 2002-10-24 2008-04-24 제너럴 일렉트릭 캄파니 Combustor Liners for Gas Turbines
JP2004144469A (en) * 2002-10-24 2004-05-20 General Electric Co <Ge> Combustor liner with inverted turbulator
EP1413829A3 (en) * 2002-10-24 2006-10-18 General Electric Company Combustor liner with inverted turbulators
US7464537B2 (en) * 2005-04-04 2008-12-16 United Technologies Corporation Heat transfer enhancement features for a tubular wall combustion chamber
US20060219191A1 (en) * 2005-04-04 2006-10-05 United Technologies Corporation Heat transfer enhancement features for a tubular wall combustion chamber
US20070264602A1 (en) * 2006-01-26 2007-11-15 Frenette Henry E Vapor fuel combustion system
US20090071160A1 (en) * 2007-09-14 2009-03-19 Siemens Power Generation, Inc. Wavy CMC Wall Hybrid Ceramic Apparatus
US7908867B2 (en) * 2007-09-14 2011-03-22 Siemens Energy, Inc. Wavy CMC wall hybrid ceramic apparatus
US8307654B1 (en) * 2009-09-21 2012-11-13 Florida Turbine Technologies, Inc. Transition duct with spiral finned cooling passage
US9657938B2 (en) 2014-02-07 2017-05-23 Eugene R. Frenette Fuel combustion system
US9874349B2 (en) 2015-04-03 2018-01-23 Eugene R. Frenette Fuel combustion system
US20230332561A1 (en) * 2020-09-16 2023-10-19 Shanghai Institute Of Space Propulsion Cryogenic engine for space apparatus
US12025075B2 (en) * 2020-09-16 2024-07-02 Shanghai Institute Of Space Propulsion Cryogenic engine for space apparatus

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