US2701445A - Ignition equipment for the combustion equipment of rocket motors - Google Patents

Ignition equipment for the combustion equipment of rocket motors Download PDF

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Publication number
US2701445A
US2701445A US240197A US24019751A US2701445A US 2701445 A US2701445 A US 2701445A US 240197 A US240197 A US 240197A US 24019751 A US24019751 A US 24019751A US 2701445 A US2701445 A US 2701445A
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United States
Prior art keywords
equipment
chamber
ignition
fuel
combustion
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
Application number
US240197A
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English (en)
Inventor
Edward G D Andrews
Anthony W T Mottram
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
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Publication of US2701445A publication Critical patent/US2701445A/en
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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 main object of this invention is to provide a satisfactory ignition equipment, for the combustion equipment of a rocket motor adapted to burn a mixture of a liquid fuel (such as methyl alcohol admixed w1th water) and a liquid oxidizer (such as liquid oxygen or nitric acid).
  • a liquid fuel such as methyl alcohol admixed w1th water
  • a liquid oxidizer such as liquid oxygen or nitric acid
  • the ignition equipment includes a precombustion or igniter chamber in which a portion of the fuel and oxidizer are combined (belng ignited by means of a spark plug or the like), and which is surrounded by a cooling jacket through which a portion of the fuel is passed to be sprayed from the outlet of the chamber.
  • Figure l is an elevation of the main chamber of the combustion equipment having attached thereto ignition equipment according to the invention.
  • Figure 2 is a sectional elevation, and Figure 3 an end elevation, of the ignition equipment
  • Figure 4 is a fragmentary view, to a larger scale, mainly of the outlet end of the igniter chamber.
  • the drawing shows the invention in a form which is intended for use in a rocket motor adapted to be operated as disclosed in the specication of co-pending patent application Serial No. 240,216 tiled August 3, 1951, and having combustion equipment arranged as therein disclosed.
  • the ignition equipment 8 includes an igniter chamber 9 communicating with the main chamber 10 of the combustion equipment such that the jet of flame issuing from the outlet 11 of the igniter chamber will meet the main supplies of liquid fuel and oxidizer delivered to the main chamber, thereby igniting these main supplies.
  • the main chamber is provided with a jacket 12 through the jacket space of which is circulated fuel i supplied thereto by the pipe 13, the outlet end of the jacket space being connected by a pipe 14 to an annular spray device coaxial with a spray device for the oxidizer supplied by a pipe 15.
  • the actual igniter chamber is formed as a shell, for 7 example, of stainless steel, which is cylindrical at 17 for about half its length and is then connected by a substantially truste-conical portion 18 to the short outlet 11 which is also cylindrical.
  • This shell is spaced within and with quite a small clearance from a correspondinglyshaped jacket wall 19 of the ignition equipment, the wall being built up of a main part 19a, a nozzle part 19b, and a uniting sleeve 19e.
  • connections 20, 21 for delivering liquid fuel and oxidizer respectively to orifices 22 through which they are sprayed, the sprays meeting one another near that end of the ignitor chamber and in the vicinity also of the operative end of a spark plug or the like 23 inserted through a hole 24 in the wall of the ignition equipment for initiating the pilot ame when starting up.
  • this cooling fuel has obtained a considerable swirl velocity by the time it leaves the jacket to join the burning gases issuing from the outlet 11 of the igniter chamber.
  • the fuel leaving the jacket space is subject to an ejector action by reason of the elllux of gases from the outlet 11 of the igniter chamber, the frusto-conical portion 18, as well as the expansion due to combustion wthin the chamber 10, ensuring a high velocity for this e ux.
  • the total igniter fuel may be about 3% to 5% of the main fuel supply t0 the combustion equipment.
  • ignition equipment including an igniter chamber which is substantially cylindrical for about half its length and is then connected by a substantially frusto-conical portion to a short outlet to communicate with the combustion equipment, said frusto-conical portion and short outlet accelerating the ow of the burning gases from the cylindrical portion of said igniter chamber, means for supplying a portion of the fuel and oxidizer to said chamber, means for igniting the fuel and oxidizer supplied thereto, a jacket around said chamber, and means for circulating another portion of the fuel through the jacket space to cool the igniter chamber and to be preheated thereby, said jacket having an outlet for connection to the combustion equipment and surrounding with clearance said short outlet and from which the preheated jacket fuel is entrained by an ejector action by the burning gases passing out of said short outlet from said igniter chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
US240197A 1950-09-08 1951-08-03 Ignition equipment for the combustion equipment of rocket motors Expired - Lifetime US2701445A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB22157/50A GB694373A (en) 1950-09-08 1950-09-08 Ignition equipment for the combustion equipment of a rocket motor

Publications (1)

Publication Number Publication Date
US2701445A true US2701445A (en) 1955-02-08

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ID=10174856

Family Applications (1)

Application Number Title Priority Date Filing Date
US240197A Expired - Lifetime US2701445A (en) 1950-09-08 1951-08-03 Ignition equipment for the combustion equipment of rocket motors

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US (1) US2701445A (US07534539-20090519-C00280.png)
BE (1) BE508933A (US07534539-20090519-C00280.png)
GB (1) GB694373A (US07534539-20090519-C00280.png)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2831322A (en) * 1952-12-29 1958-04-22 Gen Motors Corp Injector igniter plug
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US2967224A (en) * 1956-10-08 1961-01-03 Ford Motor Co Hot wire igniter
US3077073A (en) * 1957-10-29 1963-02-12 United Aircraft Corp Rocket engine having fuel driven propellant pumps
US3143851A (en) * 1960-03-23 1964-08-11 Alwac International Inc Method and apparatus for mixing combustible fluids
US4047880A (en) * 1974-05-15 1977-09-13 Antonio Caldarelli Fluids distributor for energized-fluid systems
CN104481733A (zh) * 2014-11-28 2015-04-01 苟仲武 一种高效环保液体火箭发动机
CN108757223A (zh) * 2018-03-29 2018-11-06 北京航天动力研究所 用于考核复合材料抗氧化烧蚀性能的推力室结构及方法
WO2021242229A1 (en) * 2020-05-27 2021-12-02 Aerojet Rocketdyne, Inc. Two-piece combustor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2421364A2 (fr) * 1978-03-28 1979-10-26 Europ Propulsion Systeme d'allumage pour gaz ou liquides combustibles
US5257500A (en) * 1992-07-27 1993-11-02 General Electric Company Aircraft engine ignition system

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE522435C (de) * 1927-08-17 1931-04-09 E H Hans Holzwarth Dr Ing Verpuffungskammer, insbesondere fuer Brennkraftturbinen
US1879186A (en) * 1930-10-30 1932-09-27 Robert H Goddard Apparatus for igniting liquid fuel
US2286909A (en) * 1940-12-16 1942-06-16 Robert H Goddard Combustion chamber
US2395403A (en) * 1939-03-06 1946-02-26 Daniel And Florence Guggenheim Rotatable combustion apparatus for aircraft
US2408111A (en) * 1943-08-30 1946-09-24 Robert C Truax Two-stage rocket system
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system
US2480147A (en) * 1947-01-29 1949-08-30 Letvin Samuel Firing device for combustion apparatus
US2489716A (en) * 1946-01-12 1949-11-29 Theima Mccollum Internal-combustion heater with pilot burner
US2500334A (en) * 1944-06-19 1950-03-14 Aerojet Engineering Corp Jet motor operable by monopropellant and method of operating it
US2520751A (en) * 1944-02-19 1950-08-29 Aerojet Engineering Corp Reaction motor with fluid cooling means
US2525207A (en) * 1947-01-13 1950-10-10 Lucas Ltd Joseph Ignition torch for internal-combustion prime movers

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE522435C (de) * 1927-08-17 1931-04-09 E H Hans Holzwarth Dr Ing Verpuffungskammer, insbesondere fuer Brennkraftturbinen
US1879186A (en) * 1930-10-30 1932-09-27 Robert H Goddard Apparatus for igniting liquid fuel
US2395403A (en) * 1939-03-06 1946-02-26 Daniel And Florence Guggenheim Rotatable combustion apparatus for aircraft
US2286909A (en) * 1940-12-16 1942-06-16 Robert H Goddard Combustion chamber
US2408111A (en) * 1943-08-30 1946-09-24 Robert C Truax Two-stage rocket system
US2520751A (en) * 1944-02-19 1950-08-29 Aerojet Engineering Corp Reaction motor with fluid cooling means
US2500334A (en) * 1944-06-19 1950-03-14 Aerojet Engineering Corp Jet motor operable by monopropellant and method of operating it
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system
US2489716A (en) * 1946-01-12 1949-11-29 Theima Mccollum Internal-combustion heater with pilot burner
US2525207A (en) * 1947-01-13 1950-10-10 Lucas Ltd Joseph Ignition torch for internal-combustion prime movers
US2480147A (en) * 1947-01-29 1949-08-30 Letvin Samuel Firing device for combustion apparatus

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter
US2831322A (en) * 1952-12-29 1958-04-22 Gen Motors Corp Injector igniter plug
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US2967224A (en) * 1956-10-08 1961-01-03 Ford Motor Co Hot wire igniter
US3077073A (en) * 1957-10-29 1963-02-12 United Aircraft Corp Rocket engine having fuel driven propellant pumps
US3143851A (en) * 1960-03-23 1964-08-11 Alwac International Inc Method and apparatus for mixing combustible fluids
US4047880A (en) * 1974-05-15 1977-09-13 Antonio Caldarelli Fluids distributor for energized-fluid systems
CN104481733A (zh) * 2014-11-28 2015-04-01 苟仲武 一种高效环保液体火箭发动机
CN108757223A (zh) * 2018-03-29 2018-11-06 北京航天动力研究所 用于考核复合材料抗氧化烧蚀性能的推力室结构及方法
WO2021242229A1 (en) * 2020-05-27 2021-12-02 Aerojet Rocketdyne, Inc. Two-piece combustor

Also Published As

Publication number Publication date
GB694373A (en) 1953-07-22
BE508933A (US07534539-20090519-C00280.png)

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