GB719301A - Improvements relating to gas turbine engines - Google Patents

Improvements relating to gas turbine engines

Info

Publication number
GB719301A
GB719301A GB970951A GB970951A GB719301A GB 719301 A GB719301 A GB 719301A GB 970951 A GB970951 A GB 970951A GB 970951 A GB970951 A GB 970951A GB 719301 A GB719301 A GB 719301A
Authority
GB
United Kingdom
Prior art keywords
fuel
chamber
main
casing
combustion chamber
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
Application number
GB970951A
Inventor
Alfred Cyril Lovesey
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB970951A priority Critical patent/GB719301A/en
Priority to CH307864D priority patent/CH307864A/en
Publication of GB719301A publication Critical patent/GB719301A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel

Abstract

719,301. Jet propulsion plant. ROLLS-ROYCE, Ltd. April 18, 1952 [April 25, 1951], No. 9709/51. Addition to 628,366. Class 110(3) [Also in Group XII] In a gas turbine engine as claimed in the parent Specification in which the exhaust gases from the turbine are reheated in reheat combustion equipment having a main fuel supply and ignition means for igniting the main fuel supply, the igni-. tion means comprising a combustion chamber to which fuel and compressed air from the main engine compressor are supplied, the chamber has restricted outlet means into the duct through which the exhaust gases are flowing so that the pressure within the combustion chamber of the ignition means is maintained approximately the same as that within the main engine combustion equipment. The invention is shown apphed in the case of a gas turbine jet propulsion engine, but is also applicable in the case where exhaust gases are reheated between turbines or between turbine stages. In the embodiment shown in Fig. 2, the ignition means comprises a combustion chamber 20 having a flame tube 23 therein, the chamber receiving air from the engine compressor through the hollow struts 21 from the manifold 22, and fuel through the pipe 25 and nozzle 24. The outlet from the chamber is through narrow slits 29a and hollow outwardly-extending arms 29 to an annular combustion stabilizing ring 30. The downstream edges of the arms 29 are also perforated or formed with continuous slots. The main reheat fuel is supplied through injectors 31 upstream of the chamber 20. In a second embodiment, the combustion chamber casing is of conical form with the base downstream, the outlet from the chamber being through a narrow annular gap around the base. In the embodiment shown in Fig. 4, the combustion chamber of the ignition means comprises a casing 56 in which is disposed a flame tube 58, the outlet from the flame tube being through nozzles 59 which discharge through apertures 60 in the casing 56. Fuel is supplied to the flame tube through the injector 55 and a pilot supply of fuel is also discharged through the nozzle 48. The main supply of reheat fuel is through the pipe 51 and perforated radial arms 54. An annular flame stabilizing ring 53 is disposed in the duct 13, being supported from the casing 56 by V-section struts 61 of which there is one for each aperture 60.
GB970951A 1951-04-25 1951-04-25 Improvements relating to gas turbine engines Expired GB719301A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB970951A GB719301A (en) 1951-04-25 1951-04-25 Improvements relating to gas turbine engines
CH307864D CH307864A (en) 1951-04-25 1952-08-26 Gas turbine plant.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB970951A GB719301A (en) 1951-04-25 1951-04-25 Improvements relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB719301A true GB719301A (en) 1954-12-01

Family

ID=9877266

Family Applications (1)

Application Number Title Priority Date Filing Date
GB970951A Expired GB719301A (en) 1951-04-25 1951-04-25 Improvements relating to gas turbine engines

Country Status (2)

Country Link
CH (1) CH307864A (en)
GB (1) GB719301A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1051071B (en) * 1955-07-13 1959-02-19 Sud Aviation Combustion device for supersonic ramjet engines

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1074920B (en) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Method and device for regulating gas turbine combustion chambers with subdivided combustion and several pressure levels
FR1141587A (en) * 1956-01-23 1957-09-04 Snecma Improvements to the combustion devices of continuous flow internal combustion machines
DE1123163B (en) * 1958-05-23 1962-02-01 Gen Electric Recoil engine with afterburners
DE1133185B (en) * 1959-04-21 1962-07-12 Snecma Combustion device on recoil engines, especially for post-combustion
DE1127152B (en) * 1959-09-18 1962-04-05 Bristol Siddeley Engines Ltd Air jet engine with an afterburner device in the jet pipe
FR1408812A (en) * 1964-07-06 1965-08-20 Nord Aviat Improvements in thruster combustion chambers

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1051071B (en) * 1955-07-13 1959-02-19 Sud Aviation Combustion device for supersonic ramjet engines

Also Published As

Publication number Publication date
CH307864A (en) 1955-06-15

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