US2825205A - Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft - Google Patents

Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft Download PDF

Info

Publication number
US2825205A
US2825205A US442764A US44276454A US2825205A US 2825205 A US2825205 A US 2825205A US 442764 A US442764 A US 442764A US 44276454 A US44276454 A US 44276454A US 2825205 A US2825205 A US 2825205A
Authority
US
United States
Prior art keywords
compressor
gas turbine
aircraft
air
turbine engines
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
US442764A
Inventor
Racine Gilbert
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Application granted granted Critical
Publication of US2825205A publication Critical patent/US2825205A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/24—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants of the fluid-screen type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine

Definitions

  • the fluid screen or screens may be supplied from a source of air derived from the compressor of the engine.
  • This arrangement is convenient in practice when it is a question of stabilizing a combustion within an atmosphere in which the static pressure is lower than the total pressure at the delivery side of the compressor, as is the case in particular with an intermediate combustion chamber placed after the first stage of the turbine, or of an after-burning chamber.
  • the present invention is directed to the application of fluid screens or jets to combustion chambers which operate under the pressure obtaining at the delivery side of the compressor, such as is the case of the chambers which precede the turbine.
  • the supply arrangement for these screens or jets comprises compression means adapted to deliver the gas necessary for the formation of the screens or of the jets under a pressure greater than that supplied by the air compressor of the engine.
  • the preferred form of embodiment of the invention is that in which the air which supplies the screens, derived from the compressor of the engine, is delivered by a small supplementary compressor of the centrifugal type towards the nozzle or nozzles which form the screens or the jets.
  • Fig. 1 is a view in partial cross-section of a reaction propulsion unit provided witha form of embodiment of the invention.
  • Fig. 2 shows to a larger scale a combustion chamber with its device for forming a fluid screen.
  • the air compressor of the engine shown to be of the, multi-stage 2,825,205 Patented Mar. 4, 1958 axial-flow type in the present example.
  • This compressor takes in atmospheric air through the annular passage 2 and delivers it into the combustion chambers 3, which have the shape of small barrels and are provided with fuel injectors 4.
  • the gas'generated in these chambers' is applied'to the turbine 5 which drives the compressor 1.
  • the gas discharged from the turbine escapes through the nozzle 6 which may or may not be preceded by an afterburning chamber. 7 v
  • these stabilizers consist of a hollow ring 7 on thedownstream side of each of the injectors 4,the latter being arranged'to discharge the fuel in the direction opposite to that of the air-flow, the hollow ring having a streamlined cross-section pierced with holes 8 or with one or a plurality of slots through which escapes the air which is led into the interior of the ring 7 under a total pressure higher than the static pressure of the gas passing through the combustion chamber.
  • the orifices 3 of the ring 7 are preferably oriented in such manner that the jet of gas which escapes from them has sufficient penetration into the fluid in movement to setup on the downstream side of the injector, fluid screens which create a turbulene zone in which the flame can be stabilized.
  • the said orifices 8 may be slightly inclined towards the upstream side of the flow for that purpose.
  • the rings 7 are combined with other rings 7a, the diameter of which is a little greater and which are also provided with orifices 8a through which also pass jets of air directed transversely with respect to the flow in the combustion chamber, and which have the effect of accelerating the transverse propagation of the flame, that is to say of increasing the liveliness of the combustion.
  • the hollow rings 7 and 7a are supplied with air under pressure provided by the annular collector 9 and the pipes 10 of the delivery of a small centrifugal compressor 11.
  • the intake of this supplementary compressor 11 communicates through the pipe 12 with an annular collector 13 which is arranged around the outlet of the main compressor 1 and communicates with this outlet by a slot 13a or a series of holes.
  • the air supplied to the hollow bodies 7 and 7a is thus raised to a total pressure which is higher than the static pressure obtaining in the chambers 3.
  • the ratio of compression of the compressor 11 is chosen in dependence on the size which it is desired to give to the fluid screens.
  • the compressor 11 is driven by a small gas turbine 14 to which is supplied a portion of the hot gases generated in the chambers 3.
  • the admission side of this auxiliary turbine communicates by means of a pipe 15 with an annular collector 16 arranged around the admission of the main turbine 5 and communicating with this admission by a series of holes or by a slot 1611 which may or may not be continuous;
  • the gases escaping from the turbine 14 may supply a small exhaust nozzle 17 which adds its effect to that of the main discharge nozzle 6.
  • centrifugal compressor shown in the drawings may be replaced by a compressor of any other type, axial, volumetric, etc.
  • a flame-holding device comprising an auxiliary compressor which discharges fluid at a pressure substantially in excess of the dis i charge pressure of said air compressor, and jet forming means connected with the discharge of said auxiliary compressor and opening into said combustion chamber at a substantial inclination with respect to the direction of said axial flow therethrough to form across a portion of said flow transverse fluid jets creating therebehind a wake zone wherein a flame can be held.
  • a device as claimed in claim 1 further comprising piping means for tapping a fraction of the air discharged by the compressor of the engine and leading this air to the suction end of the auxiliary compressor.
  • a device as claimed in claim 2 further comprising a gas turbine drivingly connected with the auxiliary compressor, piping means for tapping a fraction of the motive gas generated in the combustion chamber and leading this gas to the intake end of said turbine, and a rearwardly facing jet propulsion nozzle connected with the discharge end of said turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

March 4, 1958 GJRACINE 2,325,205 COMBUSTION DEVICES ESPECIALLY SUITABLE FOR GAS TURBINE ENGINES AND PROPULSION UNITS FOR AIRCRAFT Filed July 12, 1954 2 Sheets-Sheet 1 INUE-IYTOR 7,W,%,M ATmR rvEys' I d f N. Esp; 2:3. z a I I v I March 4, 1958 RACINE 2,
COMBUSTION DEVICES E CIALLY SUITABLE FOR GAS TURBINE ENGINES AND PROPULSION UNITS FOR AIRCRAFT Filed July 12, 1954 2 Sheets-Sheet 2 I/vyEvToR P (ix-W, (A A-s41, kW.
' J ATToR my;
United States Patent COMBUSTION DEVICES ESPECIALLY SUITABLE FOR GAS TURBINE ENGINES AND PROPUL- SION UNITS FOR AIRCRAFT Gilbert Racine, Paris, France, assignor to Societe Natio'nale dEtude et de Construction'de Moteurs dAvi- 'ation, Paris, France, a French company Application July 12, 1954, Serial No. 442,764
Claims priority,- application France July 15, 1953 '3 Claims. '(Cli60---39.15)
In the U. S. patent application SerQNo. 379,663, filed f September 11,- 1953, thereis'described-means ofgenerating fiuidsc'reens in the heart of a flow of gas irl which it is desired to produce a combustion, the said screens enabling a turbulent zone to be set up in the flow, with consequent reduction in speed, in which the flame can be stabilized, these screens thus replacing in an advantageous manner the normal types of stabilizing screens constituted by solid walls.
On the other hand, in the U. S. patent application Ser. No. 427,114, filed May 3, 1954, there is described the application to the development of a flame which has already been stabilized in any particular manner, of means adapted to produce transversely with respect to the front zone of the flame, small auxiliary gaseous jets which create in the flow of fluid a partial turbulence which facilitates the transverse propagation of the flame.
It has been stated in the application Ser. No. 379,663 referred to above, that in the case of a gas turbine engine, such as for example, a reaction propulsion unit, the fluid screen or screens may be supplied from a source of air derived from the compressor of the engine.
This arrangement is convenient in practice when it is a question of stabilizing a combustion within an atmosphere in which the static pressure is lower than the total pressure at the delivery side of the compressor, as is the case in particular with an intermediate combustion chamber placed after the first stage of the turbine, or of an after-burning chamber.
The present invention is directed to the application of fluid screens or jets to combustion chambers which operate under the pressure obtaining at the delivery side of the compressor, such as is the case of the chambers which precede the turbine. In accordance with the invention, the supply arrangement for these screens or jets comprises compression means adapted to deliver the gas necessary for the formation of the screens or of the jets under a pressure greater than that supplied by the air compressor of the engine.
The preferred form of embodiment of the invention is that in which the air which supplies the screens, derived from the compressor of the engine, is delivered by a small supplementary compressor of the centrifugal type towards the nozzle or nozzles which form the screens or the jets.
The description which follows below with regard to the attached drawings (which are given by way of example only and not in any sense by way of limitation) will make it quite clear how the invention may be carried into eifect, the special features which may be brought out, either from the drawings or from the text, being understood to form a part of the said invention.
Fig. 1 is a view in partial cross-section of a reaction propulsion unit provided witha form of embodiment of the invention.
Fig. 2 shows to a larger scale a combustion chamber with its device for forming a fluid screen.
In the drawings, there is to be seen at 1 the air compressor of the engine, supposed to be of the, multi-stage 2,825,205 Patented Mar. 4, 1958 axial-flow type in the present example. This compressor takes in atmospheric air through the annular passage 2 and delivers it into the combustion chambers 3, which have the shape of small barrels and are provided with fuel injectors 4. The gas'generated in these chambers'is applied'to the turbine 5 which drives the compressor 1. The gas discharged from the turbine escapes through the nozzle 6 which may or may not be preceded by an afterburning chamber. 7 v
In order tovstabilize the flame in the chambers 3, in
spite of the speed of the flow of air passing through these chambers, flame-stabilizers of 'thefiuid screen type have been provided in them.
In the example shown, these stabilizers consist of a hollow ring 7 on thedownstream side of each of the injectors 4,the latter being arranged'to discharge the fuel in the direction opposite to that of the air-flow, the hollow ring having a streamlined cross-section pierced with holes 8 or with one or a plurality of slots through which escapes the air which is led into the interior of the ring 7 under a total pressure higher than the static pressure of the gas passing through the combustion chamber. The orifices 3 of the ring 7 are preferably oriented in such manner that the jet of gas which escapes from them has sufficient penetration into the fluid in movement to setup on the downstream side of the injector, fluid screens which create a turbulene zone in which the flame can be stabilized. The said orifices 8 may be slightly inclined towards the upstream side of the flow for that purpose.
The rings 7 are combined with other rings 7a, the diameter of which is a little greater and which are also provided with orifices 8a through which also pass jets of air directed transversely with respect to the flow in the combustion chamber, and which have the effect of accelerating the transverse propagation of the flame, that is to say of increasing the liveliness of the combustion.
In the example shown, the hollow rings 7 and 7a are supplied with air under pressure provided by the annular collector 9 and the pipes 10 of the delivery of a small centrifugal compressor 11. The intake of this supplementary compressor 11 communicates through the pipe 12 with an annular collector 13 which is arranged around the outlet of the main compressor 1 and communicates with this outlet by a slot 13a or a series of holes. By virtue of the compressor 11, the air supplied to the hollow bodies 7 and 7a is thus raised to a total pressure which is higher than the static pressure obtaining in the chambers 3. The ratio of compression of the compressor 11 is chosen in dependence on the size which it is desired to give to the fluid screens.
It is an advantage to provide, in the air supply conduits of the rings 7 and 7a, one or a number of injectors 4a which enable the air to be carburetted by injecting into it a part of the fuel which is to be burnt in the chambers 3. In this Way, the combustion i given an improved uniformity inside these chambers.
In the example considered, the compressor 11 is driven by a small gas turbine 14 to which is supplied a portion of the hot gases generated in the chambers 3. The admission side of this auxiliary turbine communicates by means of a pipe 15 with an annular collector 16 arranged around the admission of the main turbine 5 and communicating with this admission by a series of holes or by a slot 1611 which may or may not be continuous; The gases escaping from the turbine 14 may supply a small exhaust nozzle 17 which adds its effect to that of the main discharge nozzle 6.
It will of course be understood that modifications may be made to the form of embodiment which has just been described, in particular by the substitution of equivalent technical means, without thereby departing from the spirit or from the scope of the present invention. The
centrifugal compressor shown in the drawings may be replaced by a compressor of any other type, axial, volumetric, etc.
What I claim is:
.1. In a jet propulsion engine having a tubular and substantially unobstructed combustion chamber and an air compressor connected to discharge thereinto an axial flow of air at flame-extinguishing velocity, a flame-holding device comprising an auxiliary compressor which discharges fluid at a pressure substantially in excess of the dis i charge pressure of said air compressor, and jet forming means connected with the discharge of said auxiliary compressor and opening into said combustion chamber at a substantial inclination with respect to the direction of said axial flow therethrough to form across a portion of said flow transverse fluid jets creating therebehind a wake zone wherein a flame can be held.
2. A device as claimed in claim 1 further comprising piping means for tapping a fraction of the air discharged by the compressor of the engine and leading this air to the suction end of the auxiliary compressor.
3. A device as claimed in claim 2 further comprising a gas turbine drivingly connected with the auxiliary compressor, piping means for tapping a fraction of the motive gas generated in the combustion chamber and leading this gas to the intake end of said turbine, and a rearwardly facing jet propulsion nozzle connected with the discharge end of said turbine.
References Cited in the file of this patent UNITED STATES PATENTS 2,374,239 Sedille Apr. 24, 1945 2,548,087 Williams Apr. 10, 1951 2,659,201 Krejci Nov. 17, 1953 FOREIGN PATENTS 225,427 Switzerland May 1, 1943 619,251 Great Britain Mar. 7, 1949 626,174 Great Britain July 11, 1949 627,644 Great Britain Aug. 12, 1949 645,588 Great Britain Nov. 1, 1950
US442764A 1953-07-15 1954-07-12 Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft Expired - Lifetime US2825205A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2825205X 1953-07-15

Publications (1)

Publication Number Publication Date
US2825205A true US2825205A (en) 1958-03-04

Family

ID=9689084

Family Applications (1)

Application Number Title Priority Date Filing Date
US442764A Expired - Lifetime US2825205A (en) 1953-07-15 1954-07-12 Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft

Country Status (1)

Country Link
US (1) US2825205A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US3410093A (en) * 1967-05-26 1968-11-12 Ghougasian John Nazareth Reaction thrust engine with fluid operated compressor
US3486699A (en) * 1965-11-22 1969-12-30 Snecma Adjustable exhaust unit for turbojet propulsion engines
US20150013339A1 (en) * 2012-03-26 2015-01-15 Alstom Technology Ltd Mixing arrangement for mixing a fuel with a stream of oxygen containing gas

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH225427A (en) * 1941-06-26 1943-01-31 Maschf Augsburg Nuernberg Ag Propellant gas generation plant, in particular for gas turbines.
US2374239A (en) * 1941-03-29 1945-04-24 Sedille Marcel Henri Louis Gas turbine installation
GB619251A (en) * 1946-11-27 1949-03-07 Donald Louis Mordell Improvements relating to combustion-equipment
GB626174A (en) * 1946-03-15 1949-07-11 Bataafsche Petroleum Improvements relating to combustion turbines
GB627644A (en) * 1947-05-06 1949-08-12 Donald Louis Mordell Improvements relating to gas-turbine-engines and combustion-equipment therefor
GB645588A (en) * 1948-10-13 1950-11-01 Karl Baumann Improvements in or relating to gas turbine power plants
US2548087A (en) * 1950-01-21 1951-04-10 A V Roe Canada Ltd Vaporizer system for combustion chambers
US2659201A (en) * 1947-11-26 1953-11-17 Phillips Petroleum Co Gas turbine combustion chamber with provision for turbulent mixing of air and fuel

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2374239A (en) * 1941-03-29 1945-04-24 Sedille Marcel Henri Louis Gas turbine installation
CH225427A (en) * 1941-06-26 1943-01-31 Maschf Augsburg Nuernberg Ag Propellant gas generation plant, in particular for gas turbines.
GB626174A (en) * 1946-03-15 1949-07-11 Bataafsche Petroleum Improvements relating to combustion turbines
GB619251A (en) * 1946-11-27 1949-03-07 Donald Louis Mordell Improvements relating to combustion-equipment
GB627644A (en) * 1947-05-06 1949-08-12 Donald Louis Mordell Improvements relating to gas-turbine-engines and combustion-equipment therefor
US2659201A (en) * 1947-11-26 1953-11-17 Phillips Petroleum Co Gas turbine combustion chamber with provision for turbulent mixing of air and fuel
GB645588A (en) * 1948-10-13 1950-11-01 Karl Baumann Improvements in or relating to gas turbine power plants
US2548087A (en) * 1950-01-21 1951-04-10 A V Roe Canada Ltd Vaporizer system for combustion chambers

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US3486699A (en) * 1965-11-22 1969-12-30 Snecma Adjustable exhaust unit for turbojet propulsion engines
US3410093A (en) * 1967-05-26 1968-11-12 Ghougasian John Nazareth Reaction thrust engine with fluid operated compressor
US20150013339A1 (en) * 2012-03-26 2015-01-15 Alstom Technology Ltd Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
US9822981B2 (en) * 2012-03-26 2017-11-21 Ansaldo Energia Switzerland AG Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
EP2831507B1 (en) * 2012-03-26 2019-12-18 Ansaldo Energia Switzerland AG Mixing arrangement for mixing a fuel with a stream of oxygen containing gas

Similar Documents

Publication Publication Date Title
US1375601A (en) Propelling device for use on vehicles, marine vessels, or aircraft
US3525474A (en) Jet pump or thrust augmentor
US2979899A (en) Flame spreading device for combustion equipments
US2168726A (en) Propulsion of aircraft and gas turbines
US2546432A (en) Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
GB780493A (en) Improvements relating to combustion equipment for gas-turbine engines
US2799991A (en) Afterburner flame stabilization means
GB757496A (en) Improvements in arrangement for controlling the air-intake orifices of jet propulsion units
US2734341A (en) Reheating turbine exhaust gases
US2439273A (en) Turbo-jet engine for aircraft
US3483699A (en) Fuel injector for a gas turbine engine
US2771743A (en) Gas-turbine engine with reheat combustion equipment
US2851859A (en) Improvements in combustion chambers for turbo-jet, turbo-prop and similar engines
US2999672A (en) Fluid mixing apparatus
US3095694A (en) Reaction motors
US2825205A (en) Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft
US3286469A (en) Rocket nozzle cooling and thrust recovery device
US3046731A (en) Flame stabilization in jet engines
US3020709A (en) Control means of the flow of a fluid by another flow
US2860483A (en) Apparatus for burning fluid fuel in a high velocity air stream with addition of lower velocity air during said burning
US2834183A (en) Composite ramjet-pulsejet engine
US3514954A (en) Gas turbine by-pass engine
US2944391A (en) Ram-jet unit
US3750400A (en) Self-starting air flow inducing reaction motor
US2639581A (en) Apparatus for burning fuel in a high velocity gas stream