US2574495A - Flame igniter for jet propulsion units - Google Patents
Flame igniter for jet propulsion units Download PDFInfo
- Publication number
- US2574495A US2574495A US594129A US59412945A US2574495A US 2574495 A US2574495 A US 2574495A US 594129 A US594129 A US 594129A US 59412945 A US59412945 A US 59412945A US 2574495 A US2574495 A US 2574495A
- Authority
- US
- United States
- Prior art keywords
- combustion chamber
- fuel
- valve
- supply
- main
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Definitions
- the present invention is particularly directed to an improved starter for liquid jet propulsion units and has as one object the provision of compact means supplying a pilot flame to positively ignite the propellants, which means is loperated independently of the main fuel nozzle.
- An additional object of the present invention isvto provide in a jet propulsion starter assembly, combined fluid flow control means and spark producing means which may be operated to furnish the initial heat of combustion Ifor propulsion starting purposes.
- a further object is to provide an independent liquid propellant igniting and burning device continued operation of which serves to protect portions of the starter mechanism from damage by the heat of normal combustion.
- Fig. 1 illustrates a schematic fuel system partially in vertical cross-section showing one embodiment of the present invention.
- Fig. 2 is a schematic fuel system showing another embodiment of the present invention.
- the system employed may comprise a high pressure tank I0 containing a suitable gas under very high pressure the discharge of which through line Il may be controlled by means of reducing valve I2.
- the gas under high pressure then passes to a T connection I3 where it 'is distributed through lines I4 and I5, as shown.
- Line I4 applies pressure to a main propellant fuel tank I6 while through line I5 pressure is applied to a liquid propellant or oxidizer tank l1.
- Discharge of propellant liquid from these tanks through lines i8 and i9 may be controlled simultaneously by electrically operated valves 20 and 2l to permit the contents to be directed into the usual liquid combining nozzle 22.
- a suitable electrical switch 21a may be provided so as to operate the valves 20 and 2
- 'I'he nozzle 22 discharges into an enlarged spherical combustion chamber 23, as shown, and the propellant liquids when they are ignited forcefully expand and emerge through jet propulsion nozzle 24 to provide the desired propulsion effect.
- a T connection 25 may be provided leading a portion of the contents from the main fuel tank I6 through line 26 where its flow is controlled by means of a separate electrically controlled igniter valve 21, the operation of which may likewise be controlled by means of a suitable electrical circuit including switch 28, as shown. Fuel from valve 21 is then conducted through line 29 to an annular recess 30 in a starter valve seat housing 3l.
- the starter mechanism of the present invention comprises the valve seat housing 3l which is provided with a plurality of seat encircling apertures 32 leading from the annular recess 30 and through which liquid propellant from tank I6 is projected into the combustion chamber 23.
- a separate motor driven blower 33 which forces air through conduit 34 into the space 35 within the valve seat housing and from the lower portion of which it emerges to mix with the liquid fuel emerging from the inwardly directed apertures 32 rforming therewith a suitable combustible mixture.
- An inlet valve 3G having a head 31 may be employed to control the air flow in a manner hereinafter to be described.
- a high tension electric spark may be caused to jump from the head 31 of the valve to a seat 38 thereby igniting the fuel and air mixture.
- This high tension current may be supplied in any desired manner as well known in the art through a suitable cable 39 which is connected to the upper end of the stem of valve 31.
- This stem is mounted for vertical reciprocation in a block 40 of suitable insulating material and is surroundedby a compression 4spring ll which bears against washer 42 secured on the stem and normallyfurges the valve into the open position as shown.
- valve I2 is flrst opened to permit pressure to be applied to the liquid propellant in tanks I6 and
- the electrically. operated blower 33 may be started as by means of the electrical circuit 28a whereby it will deliver air through conduit 3l so that it emerges 'through the angular space surrounding the valve.
- a high voltage current may beA supplied through conductor 39 and be caused to jump across the space from the head 31 of the valve to seat 38 effecting instantaneous ignition of the combined fuel and air mixture.
- With the pilot flames produced and in operation as above described valves 20 and 2
- the liquid propellants so supplied are immediately ignited by the intense heat already existing within the combustion chamber 23 by reason of the pilot iiame.
- the greatly increased temperature and resulting rise in pressure is now sufficient to overcome spring 4
- liquid fuel is supplied to the valve seat during the entire jet operation and emerges from the apertures 32 being directed by these apertures in a spray over the valve head 31.
- the eilect of this operation is to blanket or protect the valve head 31 from the heat, cooling the head and preventing warping or other deleterious effects as a result of this heat.
- When valves 28 and 2
- the igniter heretofore described may be adapted for use with a monopropellant such for example as nitromethane (CHaNOz).
- a monopropellant such for example as nitromethane (CHaNOz).
- CHaNOz nitromethane
- the nitromethane takes the place of both the fuel and the oxidizer and may be stored in a single fuel tank or there may be provided a monopropellant tank 50 and an ignitor fuel tank which later may contain 4 either the monopropellant or a separate igniter fluid.
- the monopropellant may be led from tank 50 through line 52 controlled by valve 53 which may be remotely operated by means of switch 54. Monopropellant is thus conducted to the main fuel nozzle 22 in the manner hereinbefore described with regard to the first embodiment.
- Fig. 2 the igniter fuel tank 5
- the device of the second embodiment whether employing monopropellant or some other fluid for ignition purposes, conducts fuel from tank 5
- means for initiating ignition 0f said main charge comprising a combustion chamber, means for delivering a liquid fuel supply into the combustion chamber, means for delivering an oxygen supply into the combustion chamber to form an ignitable mixture with the liquid fuel supply, means in said combustion chamber for controlling the oxygen supply comprising a movable valve at the outlet from said oxygen delivery means normally biased inwardly in the open position, and means for igniting the mixture to provide an initial combustion flame for subsequent ignition of the main charge.
- an apparatus for producing jet reaction motive force having a combustion chamber wherein a non-spontaneously ignitable main. combustible charge is injected and burned, means for initiating ignition of said main charge comprising means for delivering a liquid fuel supply into said combustion chamber, means for delivering an oxygen supply into said combustion chamber to form an ignitable mixture with the liquid fuel supply, means in said combustion chamber for controlling the oxygen supply comprising a movable valve at the outlet from said oxygen delivery means normally biased inwardly in the open position from its seat and electrical means for igniting the mixture including the movable oxygen valve whereby an electric spark is caused to jump from the valve to the adjacent valve seat.
- means for initiating ignition of the said main combustible charge comprising, means for delivering a liquid fuel supply inw said combustion chamber, means for delivering an oxygen supply into said combustion chamber for form an ignitable mixture with the liquid fuel'supply, pressure responsive means in said chamber for interrupting the oxygen supply upon combustion of the main charge, and electrical means for igniting the initial oxygen and fuel supply mixture, the pressure responsive means also serving to interrupt the electrical means upon interruption of the oxygen supply.
- valve seat assembly in communication with said combustion chamber, means for delivering a liquid fuel supply to the valve seat through a plurality of perforations forming supply ports to said combustion chamber, means for delivering an oxygen supply to the valve seat assembly and said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the control means being responsive to the pressure of combustion of the main charge within the combustion chamber, and resilient means normally rendering the control means ineffective until combustion of the main combustible charge in the chamber.
- an apparatus for producing jet reaction motive force having a combustion chamber wherein a non-spontaneously ignitable liquid main combustible charge is injected and burned, means for initiating ignition of said main charge comprising. a valve seat assembly in communication with said combustion chamber having a plurality of perforations forming supply ports for delivering liquid fuel to said combustion chamber, means for leading aliquid fuel supply to the valve seat assembly, means for leading an oxygen supply to the valve seat assembly and for delivering it into said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the control means being responsive to the pressure within said combustion chamber, and resilient means normally rendering the control means ineffective until combustion of the main combustible charge in the chamber.
- means for initiating ignition of said main charge comprising, a valve seat assembly in communication with said combustion chamber, and having a central passage and a, plurality of perforations forming supply ports for delivering liquid fuel to said combustion chamber, means for leading a liquid fuel supply to said valve seat assembly, means for leading an oxygen supply tothe valve seat assembly and for delivering it into the said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the controlmeans being responsive to the pressure within said combustion chamber, resilient means normally rendering the control means ineective until combustion of the main combustible charge in the chamber, and
- a combustion chamber means for delivering liquid fuel under pressure into the combustion chamber, means for delivering an oxidizer under pressure in the combustion chamber, a main mixing nozzle for combining the fuel and oxidizer into an ignitable mixture, a separate combustion initiating starter nozzle, means for supplying liquid fuel under pressure to the starter nozzle, means for forcing air through the starter nozzle, an igniter base having ports for delivering the liquid fuel and air simultaneously into the combustion chamber, an air control valve for automatically interrupting the air supply after ignition of the main charge, and resilient means preventing interruption of the air supply until ignition of the main charge.
- a combustion chamber means for delivering liquid fuel under pressure into the combustion chamber, means for delivering an oxidizer under pressure into the combustion chamber, a main mixing nozzle for combining the fuel and oxidizer into an ignitable mixture, a separate combustion initiating starter nozzle, means for delivering a liquid fuel supply under pressure to the starter nozzle, means for supplying air under pressure to said nozzle, an igniter base having ports for delivering the liquid fuel and air simultaneously into the combustion chamber, a
- control valve for automatically interrupting the.
- means for initiating ignition of the main charge comprising, a combustion chamber having a mixing nozzle and said main charge, means for delivering a liquid fuel supply into the combustion chamber through said mixing nozzle,
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Description
Nov. 13, 1951 F. A. PARKER, JR 2,574,495
FLAME IGNITER FOR JET PROPULSION UNITS Filed May 16, 1945 2 SI'EETSf-ISHEET 1 m g FRANK A.PARKER,JR
MWL-,Meki
Nov. 13, 1951 F. A. PARKER, JR 2,574,495
FLAME IGNITER FOR JET PROPULSION UNITS Filed May 16, 1945 2 SHEETS- SHEET 2 zflllfl/ ull.
`I lu E mf Es 9 gk 3| I LL lu I] i i :g
T g B A N SWW hln FRANK A. PARKER JR. 2l sa s;
Patented Nov. 13, 1951 UNITED FLAME IGNITER FOR JET PROPULSION UNITS Frank A. Parker, Jr., United States Navy Application May 16, 1945,`Serial No. 594,129
(Cl. Gil-39.14;)
(emma under che act of March zi, isss, n amended April 30, 1928; 370 0. G. 757) 10 Claims.
v like.
When the above propellants in combination are subjected to an intense flame they are heated sufficiently to ignite and oxidize the fuel, resulting in the desired expansion and effecting a propulsive jet from the discharge nozzle of the unit,
The present invention is particularly directed to an improved starter for liquid jet propulsion units and has as one object the provision of compact means supplying a pilot flame to positively ignite the propellants, which means is loperated independently of the main fuel nozzle.
An additional object of the present invention isvto provide in a jet propulsion starter assembly, combined fluid flow control means and spark producing means which may be operated to furnish the initial heat of combustion Ifor propulsion starting purposes.
A further object is to provide an independent liquid propellant igniting and burning device continued operation of which serves to protect portions of the starter mechanism from damage by the heat of normal combustion.
It is a further object to combine in a pilot combustion supply device means for protecting said device against the products of combustion and means for automatically terminating a portion of the pilot operation upon proper ignition K of the main -fuel charge.
Other objects and advantages will be hereinafter more fully described and for a complete understanding of the nature, scope and characteristics of this invention reference may now be had to the following description and accompanying drawings, in which latter:
Fig. 1 illustrates a schematic fuel system partially in vertical cross-section showing one embodiment of the present invention.
Fig. 2 is a schematic fuel system showing another embodiment of the present invention.
`The system employed may comprise a high pressure tank I0 containing a suitable gas under very high pressure the discharge of which through line Il may be controlled by means of reducing valve I2. The gas under high pressure then passes to a T connection I3 where it 'is distributed through lines I4 and I5, as shown. Line I4 applies pressure to a main propellant fuel tank I6 while through line I5 pressure is applied to a liquid propellant or oxidizer tank l1. Discharge of propellant liquid from these tanks through lines i8 and i9 may be controlled simultaneously by electrically operated valves 20 and 2l to permit the contents to be directed into the usual liquid combining nozzle 22. A suitable electrical switch 21a may be provided so as to operate the valves 20 and 2| together.
'I'he nozzle 22 discharges into an enlarged spherical combustion chamber 23, as shown, and the propellant liquids when they are ignited forcefully expand and emerge through jet propulsion nozzle 24 to provide the desired propulsion effect.
The starter mechanism of the present invention comprises the valve seat housing 3l which is provided with a plurality of seat encircling apertures 32 leading from the annular recess 30 and through which liquid propellant from tank I6 is projected into the combustion chamber 23. As the fuel so supplied must be mixed with air or another oxidizer before it can be ignited for starting purposes there is provided a separate motor driven blower 33 which forces air through conduit 34 into the space 35 within the valve seat housing and from the lower portion of which it emerges to mix with the liquid fuel emerging from the inwardly directed apertures 32 rforming therewith a suitable combustible mixture. An inlet valve 3G having a head 31 may be employed to control the air flow in a manner hereinafter to be described. l
In order to ignite the fuel and air mixture thus provided, a high tension electric spark may be caused to jump from the head 31 of the valve to a seat 38 thereby igniting the fuel and air mixture. This high tension current may be supplied in any desired manner as well known in the art through a suitable cable 39 which is connected to the upper end of the stem of valve 31. This stem is mounted for vertical reciprocation in a block 40 of suitable insulating material and is surroundedby a compression 4spring ll which bears against washer 42 secured on the stem and normallyfurges the valve into the open position as shown.
In operation, valve I2 is flrst opened to permit pressure to be applied to the liquid propellant in tanks I6 and |1. No propellant can pass through valves 28 and 2| since they are closed, however, liquid fuel may pass through line 2B to valve 21. Valve 21 may then be opened by the operation of switch 28 to permit fuel under pressure to flow through line 28 and emerge from the inwardly directed apertures 32 which surround the valve seat.
Simultaneously with the above described procedure the electrically. operated blower 33 may be started as by means of the electrical circuit 28a whereby it will deliver air through conduit 3l so that it emerges 'through the angular space surrounding the valve.
Concurrently with the above a high voltage current may beA supplied through conductor 39 and be caused to jump across the space from the head 31 of the valve to seat 38 effecting instantaneous ignition of the combined fuel and air mixture. I
It will be apparent that the combustion thus occurring within the combustion chamber slightly increases the pressure therein, however, spring 4| is of suflicient strength to prevent the valve from being closed by the amount of pressure so created.
With the pilot flames produced and in operation as above described valves 20 and 2| may thereupon be opened by operation of electrical control switch 2la so that liquid fuel and oxidizing mixture in the desired proportions may be forced from supply chambers I8 and I1 into the discharge nozzle 22 from which they emerge into the combustion chamber 23. The liquid propellants so supplied are immediately ignited by the intense heat already existing within the combustion chamber 23 by reason of the pilot iiame. The greatly increased temperature and resulting rise in pressure is now sufficient to overcome spring 4| and forces the valve head 31 upon the seat 38.
Because of the intense temperature rise which exists within the combustion chamber 23 liquid fuel is supplied to the valve seat during the entire jet operation and emerges from the apertures 32 being directed by these apertures in a spray over the valve head 31. The eilect of this operation is to blanket or protect the valve head 31 from the heat, cooling the head and preventing warping or other deleterious effects as a result of this heat. ,l
When valves 28 and 2| are closed the propellant chamber pressure drops and permits the spring loaded valve to lift from its seat. The igniter may then be operated as before and continues to operate as desired.
In the'embodiment illustrated in Fig. 2 a modication of the present invention is shown Wherein the igniter heretofore described may be adapted for use with a monopropellant such for example as nitromethane (CHaNOz). In this embodiment the nitromethane takes the place of both the fuel and the oxidizer and may be stored in a single fuel tank or there may be provideda monopropellant tank 50 and an ignitor fuel tank which later may contain 4 either the monopropellant or a separate igniter fluid.
When separate tanks are employed the monopropellant may be led from tank 50 through line 52 controlled by valve 53 which may be remotely operated by means of switch 54. Monopropellant is thus conducted to the main fuel nozzle 22 in the manner hereinbefore described with regard to the first embodiment.
In Fig. 2 the igniter fuel tank 5| is shown connected by outlet line 55 to the igniter nozzle and the flow may be controlled by the valve 21 as was hereinbefore described with respect to the first embodiment.
vIn operation the device of the second embodiment, whether employing monopropellant or some other fluid for ignition purposes, conducts fuel from tank 5| to the ignition chamber where it is mixed with air entering through conduit 3l and by the means hereinbefore described is ignited tc provide a pilot iiame in the combustion chamber. Monopropellant subsequently injected from the main discharge nozzle may be ignited by this pilot flame. If monopropellant alone is to be used for both the ignition and mam discharge jets then obviously tanks 50 and 5| may be combined.
From the foregoing description it will be apparent to those skilled in the art that various modications thereof may be made without departing from the spirit and scope of this invention and it is desired, therefore, that the same be limited only by the scope of the appended claims.
The invention described herein may be manufacturedand used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
Having thus described the invention, what is claimed and desired to be secured by Letters Patent is:
1. In an apparatus for producing jet reaction motive force wherein a non-spontaneously ignitable main combustible charge is injected and burned, means for initiating ignition 0f said main charge comprising a combustion chamber, means for delivering a liquid fuel supply into the combustion chamber, means for delivering an oxygen supply into the combustion chamber to form an ignitable mixture with the liquid fuel supply, means in said combustion chamber for controlling the oxygen supply comprising a movable valve at the outlet from said oxygen delivery means normally biased inwardly in the open position, and means for igniting the mixture to provide an initial combustion flame for subsequent ignition of the main charge.
2. In an apparatus for producing jet reaction motive force having a combustion chamber wherein a non-spontaneously ignitable main. combustible charge is injected and burned, means for initiating ignition of said main charge comprising means for delivering a liquid fuel supply into said combustion chamber, means for delivering an oxygen supply into said combustion chamber to form an ignitable mixture with the liquid fuel supply, means in said combustion chamber for controlling the oxygen supply comprising a movable valve at the outlet from said oxygen delivery means normally biased inwardly in the open position from its seat and electrical means for igniting the mixture including the movable oxygen valve whereby an electric spark is caused to jump from the valve to the adjacent valve seat.
3. In an apparatus for producing jet reaction s motive force having a combustion chamber wherein a non-spontaneously ignitable main combustible charge is injected and burned, means for initiating ignition of the said main combustible charge comprising, means for delivering a liquid fuel supply inw said combustion chamber, means for delivering an oxygen supply into said combustion chamber for form an ignitable mixture with the liquid fuel'supply, pressure responsive means in said chamber for interrupting the oxygen supply upon combustion of the main charge, and electrical means for igniting the initial oxygen and fuel supply mixture, the pressure responsive means also serving to interrupt the electrical means upon interruption of the oxygen supply.
comprising, a valve seat assembly in communication with said combustion chamber, means for delivering a liquid fuel supply to the valve seat through a plurality of perforations forming supply ports to said combustion chamber, means for delivering an oxygen supply to the valve seat assembly and said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the control means being responsive to the pressure of combustion of the main charge within the combustion chamber, and resilient means normally rendering the control means ineffective until combustion of the main combustible charge in the chamber.
5. In an apparatus for producing jet reaction motive force having a combustion chamber wherein a non-spontaneously ignitable liquid main combustible charge is injected and burned, means for initiating ignition of said main charge comprising. a valve seat assembly in communication with said combustion chamber having a plurality of perforations forming supply ports for delivering liquid fuel to said combustion chamber, means for leading aliquid fuel supply to the valve seat assembly, means for leading an oxygen supply to the valve seat assembly and for delivering it into said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the control means being responsive to the pressure within said combustion chamber, and resilient means normally rendering the control means ineffective until combustion of the main combustible charge in the chamber.
6. In an apparatus for producing jet reaction motive force having a combustion chamber wherein a non-spontaneously ignitable liquid main combustible charge is injected and burned, means for initiating ignition of said main charge comprising, a valve seat assembly in communication with said combustion chamber, and having a central passage and a, plurality of perforations forming supply ports for delivering liquid fuel to said combustion chamber, means for leading a liquid fuel supply to said valve seat assembly, means for leading an oxygen supply tothe valve seat assembly and for delivering it into the said combustion chamber adjacent the liquid fuel supply ports, control means for interrupting the oxygen supply, the controlmeans being responsive to the pressure within said combustion chamber, resilient means normally rendering the control means ineective until combustion of the main combustible charge in the chamber, and
electric ignition means for igniting the fuel and oxygen mixture.
y '1. In an apparatus for producing jet reaction motive force wherein a non-spontaneously ignitable liquid main combustible charge is injected and burned, a combustion chamber, means for delivering liquid fuel under pressure into the combustion chamber, means for delivering an oxidizer under pressure in the combustion chamber, a main mixing nozzle for combining the fuel and oxidizer into an ignitable mixture, a separate combustion initiating starter nozzle, means for supplying liquid fuel under pressure to the starter nozzle, means for forcing air through the starter nozzle, an igniter base having ports for delivering the liquid fuel and air simultaneously into the combustion chamber, an air control valve for automatically interrupting the air supply after ignition of the main charge, and resilient means preventing interruption of the air supply until ignition of the main charge.
8. In an apparatus for producing jet reaction motive force wherein non-spontaneously ignitable liquid main combustible charge is injected and burned, a combustion chamber, means for delivering liquid fuel under pressure into the combustion chamber, means for delivering an oxidizer under pressure into the combustion chamber, a main mixing nozzle for combining the fuel and oxidizer into an ignitable mixture, a separate combustion initiating starter nozzle, means for delivering a liquid fuel supply under pressure to the starter nozzle, means for supplying air under pressure to said nozzle, an igniter base having ports for delivering the liquid fuel and air simultaneously into the combustion chamber, a
control valve for automatically interrupting the.
air supply after ignition of the main charge, resilient means preventing interruption of the air supply until ignition of the main charge, and ignition means including a movable portion of said valve for igniting the combustion initiating charge.
9. In an apparatus for producing jet reaction motive force wherein non-spontaneously ignitable liquid main combustible charge is injected and burned. means for initiating ignition of the main charge comprising, a combustion chamber having a mixing nozzle and said main charge, means for delivering a liquid fuel supply into the combustion chamber through said mixing nozzle,
means for delivering an oxygen supply into the combustion chamber through the mixing nozzle, remote control means for controlling said fuel supply means and the oxygen supply means, an igniter nozzle, means for delivering an igniter liquid fuel supply into the igniter nozzle, a separate means for delivering an oxidizer supply into the igniter nozzle, remote control means for simultaneously initiating the igniter liquid fuel supply means and igniter oxidizer supply means, means responsive to the pressure in the combustion chamber for interrupting the oxidizer supply independently of the liquid fuel supply, and means for igniting the igniter liquid fuel and oxidizer supply within the combustion chamber.
10. In an apparatus for producing jet reaction motive forces wherein a nonspontaneously ignitable liquid propellant is burned, a combustion chamber, a main fuel nozzle and an igniter fuel nozzle for said chamber, means for delivering the liquid propellant to said main fuel nozzle and means for delivering the liquid propellant to said igniter fuel nozzle, said last named means including igniter means arranged to automatically 'dlsoontlnue' operation in response to pressure of combustion of the propellant discharged by the main fuel nozzle.
FRANK A. PARKER. Jn.
REFERENCES CITED 8 v UNITED STATES PATENTS y Number Name l Date Hubbell May 31, 1927 Rogers ..-.1 June 17,1930 Goddard Sept. 27, 1932 Chandler Nov.- 8, 1932 Aldrich Dec. 6, 1932 Goddard Aug. 17, 1937 Zieler Feb. 24, 1942
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US594129A US2574495A (en) | 1945-05-16 | 1945-05-16 | Flame igniter for jet propulsion units |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US594129A US2574495A (en) | 1945-05-16 | 1945-05-16 | Flame igniter for jet propulsion units |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2574495A true US2574495A (en) | 1951-11-13 |
Family
ID=24377639
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US594129A Expired - Lifetime US2574495A (en) | 1945-05-16 | 1945-05-16 | Flame igniter for jet propulsion units |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2574495A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE941102C (en) * | 1950-09-08 | 1956-04-05 | Armstrong Siddeley Motors Ltd | Actuation and control device for the supply of liquid fuel and liquid oxygen carrier to a combustion device, especially for rocket drives |
| US2744383A (en) * | 1941-03-29 | 1956-05-08 | Rateau Soc | Gas turbine plant |
| US2749705A (en) * | 1951-01-03 | 1956-06-12 | Gen Electric | Fusible link jet motor control |
| US2751750A (en) * | 1953-10-22 | 1956-06-26 | British Thomson Houston Co Ltd | Reaction chambers for the decomposition of monofuels |
| US2766837A (en) * | 1951-11-05 | 1956-10-16 | Mccollum Burton | Seismic exploration apparatus |
| US2775865A (en) * | 1951-06-07 | 1957-01-01 | British Thomson Houston Co Ltd | Starters for prime movers such as gas turbines |
| US2810261A (en) * | 1952-10-15 | 1957-10-22 | Plessey Co Ltd | Combustion control system |
| US2859590A (en) * | 1955-02-23 | 1958-11-11 | Bendix Aviat Corp | Piston type igniter |
| US2925715A (en) * | 1958-01-31 | 1960-02-23 | John T Kenney | Combustion chamber |
| US2968152A (en) * | 1956-10-01 | 1961-01-17 | United Aircraft Corp | Air separator for monofuel burner |
| US3038530A (en) * | 1959-01-12 | 1962-06-12 | Aerojet General Co | Flame thrower |
| US3057159A (en) * | 1959-06-23 | 1962-10-09 | United Aircraft Corp | Rocket ignitor |
| US3059429A (en) * | 1958-03-25 | 1962-10-23 | Sunstrand Corp | Reaction chamber |
| US3088282A (en) * | 1956-09-14 | 1963-05-07 | Bendix Corp | Ignition apparatus |
| US3098353A (en) * | 1961-03-31 | 1963-07-23 | United Aircraft Corp | Rocket engine propellant feeding and control system |
| US3135088A (en) * | 1961-03-02 | 1964-06-02 | United Aircraft Corp | Sequencing system |
| US3750392A (en) * | 1971-12-22 | 1973-08-07 | Curtiss Wright Corp | High energy ignition device |
| US3771313A (en) * | 1970-05-12 | 1973-11-13 | Generation of motive power with metal and water as fuel | |
| US4091769A (en) * | 1977-02-25 | 1978-05-30 | Baldwin Richard J | Non-air breathing option for an internal combustion engine |
| US5088287A (en) * | 1989-07-13 | 1992-02-18 | Sundstrand Corporation | Combustor for a turbine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1630702A (en) * | 1927-05-31 | A cobpobation | ||
| US1764984A (en) * | 1924-11-22 | 1930-06-17 | Comb Fuel Oil Burner Company | Oil-burning apparatus |
| US1879186A (en) * | 1930-10-30 | 1932-09-27 | Robert H Goddard | Apparatus for igniting liquid fuel |
| US1887230A (en) * | 1925-04-18 | 1932-11-08 | Carl B Chandler | Ignition device for fuel burners |
| US1889968A (en) * | 1925-05-01 | 1932-12-06 | Preferred Oil Burners Inc | Spark ignition mechanism for domestic oil burners |
| US2090039A (en) * | 1935-05-07 | 1937-08-17 | Robert H Goddard | Igniter |
| US2274573A (en) * | 1933-12-22 | 1942-02-24 | Ziegler Serge | Oil burner |
-
1945
- 1945-05-16 US US594129A patent/US2574495A/en not_active Expired - Lifetime
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1630702A (en) * | 1927-05-31 | A cobpobation | ||
| US1764984A (en) * | 1924-11-22 | 1930-06-17 | Comb Fuel Oil Burner Company | Oil-burning apparatus |
| US1887230A (en) * | 1925-04-18 | 1932-11-08 | Carl B Chandler | Ignition device for fuel burners |
| US1889968A (en) * | 1925-05-01 | 1932-12-06 | Preferred Oil Burners Inc | Spark ignition mechanism for domestic oil burners |
| US1879186A (en) * | 1930-10-30 | 1932-09-27 | Robert H Goddard | Apparatus for igniting liquid fuel |
| US2274573A (en) * | 1933-12-22 | 1942-02-24 | Ziegler Serge | Oil burner |
| US2090039A (en) * | 1935-05-07 | 1937-08-17 | Robert H Goddard | Igniter |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2744383A (en) * | 1941-03-29 | 1956-05-08 | Rateau Soc | Gas turbine plant |
| DE941102C (en) * | 1950-09-08 | 1956-04-05 | Armstrong Siddeley Motors Ltd | Actuation and control device for the supply of liquid fuel and liquid oxygen carrier to a combustion device, especially for rocket drives |
| US2749705A (en) * | 1951-01-03 | 1956-06-12 | Gen Electric | Fusible link jet motor control |
| US2775865A (en) * | 1951-06-07 | 1957-01-01 | British Thomson Houston Co Ltd | Starters for prime movers such as gas turbines |
| US2766837A (en) * | 1951-11-05 | 1956-10-16 | Mccollum Burton | Seismic exploration apparatus |
| US2810261A (en) * | 1952-10-15 | 1957-10-22 | Plessey Co Ltd | Combustion control system |
| US2751750A (en) * | 1953-10-22 | 1956-06-26 | British Thomson Houston Co Ltd | Reaction chambers for the decomposition of monofuels |
| US2859590A (en) * | 1955-02-23 | 1958-11-11 | Bendix Aviat Corp | Piston type igniter |
| US3088282A (en) * | 1956-09-14 | 1963-05-07 | Bendix Corp | Ignition apparatus |
| US2968152A (en) * | 1956-10-01 | 1961-01-17 | United Aircraft Corp | Air separator for monofuel burner |
| US2925715A (en) * | 1958-01-31 | 1960-02-23 | John T Kenney | Combustion chamber |
| US3059429A (en) * | 1958-03-25 | 1962-10-23 | Sunstrand Corp | Reaction chamber |
| US3038530A (en) * | 1959-01-12 | 1962-06-12 | Aerojet General Co | Flame thrower |
| US3057159A (en) * | 1959-06-23 | 1962-10-09 | United Aircraft Corp | Rocket ignitor |
| US3135088A (en) * | 1961-03-02 | 1964-06-02 | United Aircraft Corp | Sequencing system |
| US3098353A (en) * | 1961-03-31 | 1963-07-23 | United Aircraft Corp | Rocket engine propellant feeding and control system |
| US3771313A (en) * | 1970-05-12 | 1973-11-13 | Generation of motive power with metal and water as fuel | |
| US3750392A (en) * | 1971-12-22 | 1973-08-07 | Curtiss Wright Corp | High energy ignition device |
| US4091769A (en) * | 1977-02-25 | 1978-05-30 | Baldwin Richard J | Non-air breathing option for an internal combustion engine |
| US5088287A (en) * | 1989-07-13 | 1992-02-18 | Sundstrand Corporation | Combustor for a turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2574495A (en) | Flame igniter for jet propulsion units | |
| US2858672A (en) | Monofuel decomposition apparatus | |
| US6469424B1 (en) | Ignitor for liquid fuel rocket engines | |
| US3065597A (en) | Reignitable solid rocket motor | |
| US2648951A (en) | Combustor igniter cup which becomes incandescent from combustion therein | |
| US3354647A (en) | Method for initiating or quenching the combustion in a solid propellant rocket motor | |
| US2741085A (en) | Safety device, including fusible member for rocket engine starting control | |
| US2397657A (en) | Control mechanism for rocket apparatus | |
| US3065596A (en) | Reignitable solid rocket motor | |
| US2689454A (en) | Rocket engine | |
| US2742758A (en) | Starter control system | |
| US3143853A (en) | Solid propellant burn area control | |
| US2743577A (en) | Rocket engine control | |
| US3065598A (en) | Reignitable solid rocket motor | |
| US2928240A (en) | Control system for reaction motor ignitors | |
| US3057159A (en) | Rocket ignitor | |
| US2998703A (en) | Reso-jet igniter | |
| GB702779A (en) | Means for supplying propellents to a rocket motor | |
| US3533233A (en) | Hot gas generator utilizing a mono-propellant fuel | |
| US3056257A (en) | Rocket ignitor construction | |
| US3128601A (en) | Pre-burner rocket control system | |
| US3472029A (en) | Gas turbine power units | |
| US3147592A (en) | Hydrazine gas generator | |
| US2465926A (en) | Sequence firing of jet motors | |
| US10451007B1 (en) | Enhanced operability dual mode ramjet and scramjet engine ignition system |