US2621477A - Combustion apparatus having valve controlled passages for preheating the fuel-air mixture - Google Patents

Combustion apparatus having valve controlled passages for preheating the fuel-air mixture Download PDF

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US2621477A
US2621477A US120476A US12047649A US2621477A US 2621477 A US2621477 A US 2621477A US 120476 A US120476 A US 120476A US 12047649 A US12047649 A US 12047649A US 2621477 A US2621477 A US 2621477A
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air
flame tube
fuel
combustion apparatus
jacket
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US120476A
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Geoffrey J Powter
Lloyd Peter
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/26—Controlling the air flow

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  • This invention relates to improvements in combustion systems, and isintended in particular for use in cases in which combustion has to be supported by a fast-moving stream of fluid (hereinafter considered as being air).
  • a fast-moving stream of fluid hereinafter considered as being air.
  • the description fast moving as applied to a combustion-supportin air stream is used herein to indicate that the mean speed of the air stream in its general direction of flow past a combustion zone, calculated from the ratio air volume passing in unit time/cross sectional area of the flow path, is sufilciently high in relation to the speed of flame propagation in the fuel/air mixture concerned to have flame extinguishing properties.
  • the speed of flame propagation is considered as being of the order of one foot per second at atmospheric temperature; the invention, on the other hand, is especially applicable to combustion apparatus for gas turbine or/and jet propulsion power units in which the speed of the air stream in its general direction of flow past a combustion zone, calculated on the basis indicated, might be from 10 to 300 feet per second or even more, depending on the design.
  • the invention is further of particular interest in relation to installations which, in common with such power units, require stabilised burning to be supported not only by a fast moving airstream but also with high air/fuel ratios. Combustion apparatus for these purposes is also required to maintain stable burnin at high rates of fuel injection with a minimum of pressure loss.
  • a further "object of the present invention is to improve the combustion performance under conditions of very low pressure such as is experienced, for example, in the case of gas turbine aero engines operating at high altitudes. Hitherto combustion under such circumstances has presented considerable difficulties owing to the fact that in such cases the simple atomi-sing burner operates at reduced efilciency and an object of the present invention is to overcome this disadvantage.
  • the valve may be located at the entry to said annular passage or at the entry connecting the passage to the interior of the flame tube, thus controlling the flow of primary air.
  • the valve may control the flow of secondary air into the flame tube.
  • Figure 1 is a diagrammatic axial cross-section of one embodiment of the invention
  • FIGS 2 and 3 are fragmentary views of two modifications of the embodiment shown in Figure 1.
  • the apparatus shown in Figure 1 comprises a substantially cylindrical flame tube I provided towards its upstream region (relative to the direction of flow of gases in the tube) with an annular envelope or jacket 2 co-axial with the tube l and having at its upstream end, incurved walls 3 which together with corresponding incurved walls 4 of the upstream end of the flame tube form arcuate passages 5 whereby the flow of fluid passing upstream through the annular envelope 2 can be reversed efiiciently and led downstream through an axial entry into the flame tube 1.
  • an outer casing 6 Surrounding the Whole of the flame tube l and the annulus 2 is an outer casing 6 which is also co-axial with the flame tube I and in combination with the latter forms a second annular space '5 around the above-mentioned annular envelope 2 and around the downstream portion ofthe flame tube I.
  • the main air-stream is led downstream into this second annular space I through a connecting duct 8 which is of frusto-conical form hav ing its narrow end upstream and its wider end downstream and arranged co-axially with the flame tube I.
  • a co-axial hollow cone 9 having its apex pointing upstream and its base abutting against the upstream end of theflame tube I thereby forming in combination with the frusto-conical duct an annular passage I9 which leads into the abovementioned second annular space I and which may constitute either a diffusing passage or an accelerating passage according to the relationship between the cross sectional area of the upstream and downstream ends II, I2 of the annular passage.
  • the downstream end of the annular envelope 2 is open and the arrangement is such that the main air stream flows in a downstream direction through the above-mentioned second annular space I and at the downstream open end of the annular envelope 2 a part of the main air stream reverses its flow path through 180 to enter the said envelope, and flow through it in an upstream direction.
  • a circular series of radially directed swirl vanes I3 by means of which the incoming air is given a swirling movement around the axis of the flame tube I.
  • One or more liquid fuel supply pipes I4 are arranged so that their delivery ends protrude into the annular envelope 2 and when liquid fuel is discharged from these ends, it impinges against the wall of the flame tube I so as to form a spray which, if this wall is hot, immediately vaporizes, the fuel vapour then mixing with the air within the envelope 2.
  • the mixture of air and fuel vapour flows upstream while at the same time swirling around the axis of the tube I and at the upstream end of the envelope 2 its path is again reversed through 189 by the incurved walls 3, 4, whereby the mixture is led through an axial entry I5 into the flame tube I in a downstream direction.
  • a spark plug It by means of which the mixture may be ignited.
  • the flame tube I is preferably provided with a portion Ia of short axial length but enlarged diameter relative to the main portion of the flame tube, which enlarged portion together with .
  • the outer casing 5 forms an annularspace I8 of very small radial dimensions relative to the annular space F. The dimensions are arranged so that through the space I8 there flows a small part (conveniently approximately per cent) of the main air stream to constitute cooling air.
  • the mixture of primary air and fuel vapour is throttled by means of a disc valve l9 located immediately upstream of this entry, the valve being supported by a stem 29 which is arranged within the cone 9 and is co-axial with the flame tube I.
  • Suitable means are provided for varying the distance between the disc I9 and the entry IE so as to obtain a variable throttle effect.
  • the disc I9 causes turbulence near the entry 5 whereby the air-fuel mixture fills the space formed by the walls 4 and thus promotes heating of the flame tube wall and vaporization of the fuel.
  • the .disc valve I9 is operated from the engine Z throttle 2I through linkage 22, 23, so that if the fuel supply is increased the distance between the valve I9 and the entry I5 is also increased so as to maintain an approximately chemically correct mixture strength in the primary combustion zone.
  • auxiliary means for injecting fuel within the flame tube I In order to initiate the combustion process it is necessary to provide auxiliary means for injecting fuel within the flame tube I and for this purpose use may be made of a pilot fuel jet or gas delivery pipe 24 which may deliver to a region in the vicinity of the spark plug IS.
  • the auxiliary fuel supply is, of course, cut off once combustion has begun and the flame tube wall has become sufficiently hot to vaporize the fuel.
  • variable throttling efiect may also be obtained by making use of difierential expansion between the tube I and the outer casing 6 to open or close one or more restricting orifices through which the mixture of air and fuel passes into the flame tube I.
  • the flame tube I is formed with an outwardly directed annular projection which forms with the end of the envelope 2 an annular passage 26 through which primary air flows to the flame tube. It will be appreciated that the flame tube I will expand to a greater extent than the envelope 2 in operation and consequentlyas the flame tube temperature increases due to an increased fuel supply, the passage 26 will also increase in size so that a greater quantity of air is admitted to the flame tube to maintain a substantially constant air/fuel ratio.
  • the proportion of air entering as mixing air through the apertures I! in theflame tube wall may be varied by making some or all of said apertures, for example by means of a sleeve ,slidable :over the flame tube.
  • FIG. 3 This is shown in Figure 3 in which the envelope 2 is extended downstream to form a sleeve 21 closely fitting over the downstream portion of the flame tube l.
  • a circular series of apertures 28 are provided for the admission of primary combustion air to the space between the envelope 2 and the flame tube I, and further apertures 29 are provided in the sleeve corresponding to the apertures I! in the flame tube. It will be seen that due to differential thermal expansion between the sleeve 21 and the flame tube I, the apertures I! will be progressively blanked off as the temperature increases. The secondary air supply is thus restricted and a greater quantity of air is constrained to enter the primary combustion zone.
  • Combustion apparatus comprising an air casing having an air inlet, a flame tube within said air casing, a tubular sheath member enclosing and radially spaced from an upstream part of the flame tube to form therewith an annular passage, :the upstream end of said member (in relation to the flow of working fluid through the flame tube) being closed and the downstream end bein open and-forming with the flame tube an annular entry for a stream of primary air from the air casing to saidannular passage, means for injecting fuel intosaid annular passage to mix with the primary air, entry means connecting the annular passage to an upstream part of the interior of the flame tube, further entry means in the wall of the flame tube downstream of said sheath member for a stream of secondary air, and a valve located in and controlling the flow of one of said streams to vary the proportions of primary and secondary air.
  • valve is operable, when the rate of delivery of fuel is varied, in a sense to maintain a substantially constant ratio between the quantitles of primary air and fuel.
  • Combustion apparatus according to claim 2 wherein said valve is operatively linked to an engine throttle.
  • Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, said entry comprising valve means controlling the flow of fuel/air mixture therethrough, and further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air.
  • Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of Working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, and further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air, and valve means controlling the flow of air/fuel mixture through the jacket, said valve means being actuated by differential thermal expansion 'be tween the flame tube and the enclosing structure.
  • Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, and further entry means including a valve in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air.
  • Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein, entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air, and valve means controlling the flow through the jacket.

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Description

Dec. 16, 1952 ow ETAL 2,621,477
COMBUSTION APPARATUS HAVING VALVE CONTROLLED PASSAGES FOR PREHEATING THE FUEL-AIR MIXTURE Filed 001'.- 10, 1949 2 SHEETS SHEET l mm Mazda o M x= w NW m 82,323 a :2 m "m 1 xw .rrf 1| L B .X N amt?! v Q m U 2 v 2 I H, I N 2 o G: N E: :2 n 25 V5; 2
Dec. 16, 1952 G. J. POWTER ETAL 2,621,477
COMBUSTION APPARATUS HAVING VALVE CONTROLLED PASSAGES FOR PREHEATING THE FUEL-AIR MIXTURE Filed 001;. 10, 1949 2 SHEETS-SHEET 2 fmzz,
5:21; Afror myg Patented Dec. 16, 1952 COMBUSTION APPARATUS HAVING VALVE CONTROLLED PASSAGES FOR PREHEAT- ING THE FUEL-AIR MIXTURE Geoffrey J. Powter, London, and Peter Lloyd, Farnham, England, assignors to Power Jets (Research and Development) Limited, London, England, a British company Application October 10, 1949, Serial No. 120,476 In Great Britain June 3, 1948 8 Claims. 1
This invention relates to improvements in combustion systems, and isintended in particular for use in cases in which combustion has to be supported by a fast-moving stream of fluid (hereinafter considered as being air). The description fast moving as applied to a combustion-supportin air stream is used herein to indicate that the mean speed of the air stream in its general direction of flow past a combustion zone, calculated from the ratio air volume passing in unit time/cross sectional area of the flow path, is sufilciently high in relation to the speed of flame propagation in the fuel/air mixture concerned to have flame extinguishing properties. For hydrocarbon fuels burning in air the speed of flame propagation is considered as being of the order of one foot per second at atmospheric temperature; the invention, on the other hand, is especially applicable to combustion apparatus for gas turbine or/and jet propulsion power units in which the speed of the air stream in its general direction of flow past a combustion zone, calculated on the basis indicated, might be from 10 to 300 feet per second or even more, depending on the design. The invention is further of particular interest in relation to installations which, in common with such power units, require stabilised burning to be supported not only by a fast moving airstream but also with high air/fuel ratios. Combustion apparatus for these purposes is also required to maintain stable burnin at high rates of fuel injection with a minimum of pressure loss.
A further "object of the present invention is to improve the combustion performance under conditions of very low pressure such as is experienced, for example, in the case of gas turbine aero engines operating at high altitudes. Hitherto combustion under such circumstances has presented considerable difficulties owing to the fact that in such cases the simple atomi-sing burner operates at reduced efilciency and an object of the present invention is to overcome this disadvantage.
Accordingly the invention provides a combustion apparatus comprising an air casing having an air inlet, a flame tube within said air casing, a tubular sheath member enclosing and radially spaced from an upstream part of the flame tube to form therewith an annular passage, the upstream end of said member (in relation to the flow of working fluid through the flame tube) being closed and the downstream end being open and forming with the flame tube an annular entry for a stream of primary air from the air casing to said annular passage, means for in= .iecting fuel into said annular passage to mix with the primary air, entry means connecting the annular passage to an upstream part of the interior of the flame tube, further entry means in the wall of the flame tube downstream of said sheath member for a stream of secondary air, and a valve located in and controlling the flow of one of said streams to vary the proportions of primary and secondary air.
The valve may be located at the entry to said annular passage or at the entry connecting the passage to the interior of the flame tube, thus controlling the flow of primary air. Alternatively the valve may control the flow of secondary air into the flame tube.
In order to maintain an approximately chemically correct mixture strength in the primary zone of the combustion system under all operating conditions, it is advantageous to vary the primary air flow for different rates of fuel supply correspcnding to different positions of the engine throttle.
The invention is more particularly described by way of example with reference to the accompanying drawings of which:
Figure 1 is a diagrammatic axial cross-section of one embodiment of the invention;
Figures 2 and 3 are fragmentary views of two modifications of the embodiment shown in Figure 1.
The apparatus shown in Figure 1 comprises a substantially cylindrical flame tube I provided towards its upstream region (relative to the direction of flow of gases in the tube) with an annular envelope or jacket 2 co-axial with the tube l and having at its upstream end, incurved walls 3 which together with corresponding incurved walls 4 of the upstream end of the flame tube form arcuate passages 5 whereby the flow of fluid passing upstream through the annular envelope 2 can be reversed efiiciently and led downstream through an axial entry into the flame tube 1.
Surrounding the Whole of the flame tube l and the annulus 2 is an outer casing 6 which is also co-axial with the flame tube I and in combination with the latter forms a second annular space '5 around the above-mentioned annular envelope 2 and around the downstream portion ofthe flame tube I.
The main air-stream is led downstream into this second annular space I through a connecting duct 8 which is of frusto-conical form hav ing its narrow end upstream and its wider end downstream and arranged co-axially with the flame tube I. Within the duct 8 is arranged a co-axial hollow cone 9 having its apex pointing upstream and its base abutting against the upstream end of theflame tube I thereby forming in combination with the frusto-conical duct an annular passage I9 which leads into the abovementioned second annular space I and which may constitute either a diffusing passage or an accelerating passage according to the relationship between the cross sectional area of the upstream and downstream ends II, I2 of the annular passage.
The downstream end of the annular envelope 2 is open and the arrangement is such that the main air stream flows in a downstream direction through the above-mentioned second annular space I and at the downstream open end of the annular envelope 2 a part of the main air stream reverses its flow path through 180 to enter the said envelope, and flow through it in an upstream direction.
Within the envelope 2 are provided a circular series of radially directed swirl vanes I3 by means of which the incoming air is given a swirling movement around the axis of the flame tube I.
One or more liquid fuel supply pipes I4, are arranged so that their delivery ends protrude into the annular envelope 2 and when liquid fuel is discharged from these ends, it impinges against the wall of the flame tube I so as to form a spray which, if this wall is hot, immediately vaporizes, the fuel vapour then mixing with the air within the envelope 2.
The mixture of air and fuel vapour flows upstream while at the same time swirling around the axis of the tube I and at the upstream end of the envelope 2 its path is again reversed through 189 by the incurved walls 3, 4, whereby the mixture is led through an axial entry I5 into the flame tube I in a downstream direction.
Within the flame tube I and a short distance downstream of the said entry is arranged a spark plug It by means of which the mixture may be ignited.
In the wall of the flame tube I and downstream of the annular envelope 2 are provided a number of apertures 11 through which a part of the main air stream enters the flame tube to constitute mixing air.
In the region of its downstream outlet, the flame tube I is preferably provided with a portion Ia of short axial length but enlarged diameter relative to the main portion of the flame tube, which enlarged portion together with .the outer casing 5 forms an annularspace I8 of very small radial dimensions relative to the annular space F. The dimensions are arranged so that through the space I8 there flows a small part (conveniently approximately per cent) of the main air stream to constitute cooling air.
At its axial entry into the flame tube I the mixture of primary air and fuel vapour is throttled by means of a disc valve l9 located immediately upstream of this entry, the valve being supported by a stem 29 which is arranged within the cone 9 and is co-axial with the flame tube I. Suitable means are provided for varying the distance between the disc I9 and the entry IE so as to obtain a variable throttle effect.
The disc I9 causes turbulence near the entry 5 whereby the air-fuel mixture fills the space formed by the walls 4 and thus promotes heating of the flame tube wall and vaporization of the fuel.
The .disc valve I9 is operated from the engine Z throttle 2I through linkage 22, 23, so that if the fuel supply is increased the distance between the valve I9 and the entry I5 is also increased so as to maintain an approximately chemically correct mixture strength in the primary combustion zone.
In order to initiate the combustion process it is necessary to provide auxiliary means for injecting fuel within the flame tube I and for this purpose use may be made of a pilot fuel jet or gas delivery pipe 24 which may deliver to a region in the vicinity of the spark plug IS. The auxiliary fuel supply is, of course, cut off once combustion has begun and the flame tube wall has become sufficiently hot to vaporize the fuel.
As an alternative to the above-mentioned disc valve I9 a variable throttling efiect may also be obtained by making use of difierential expansion between the tube I and the outer casing 6 to open or close one or more restricting orifices through which the mixture of air and fuel passes into the flame tube I.
This arrangement, is shown in Figure 2. In this case the flame tube I is formed with an outwardly directed annular projection which forms with the end of the envelope 2 an annular passage 26 through which primary air flows to the flame tube. It will be appreciated that the flame tube I will expand to a greater extent than the envelope 2 in operation and consequentlyas the flame tube temperature increases due to an increased fuel supply, the passage 26 will also increase in size so that a greater quantity of air is admitted to the flame tube to maintain a substantially constant air/fuel ratio.
As a further alternative throttling means, the proportion of air entering as mixing air through the apertures I! in theflame tube wall may be varied by making some or all of said apertures, for example by means of a sleeve ,slidable :over the flame tube.
This is shown in Figure 3 in which the envelope 2 is extended downstream to form a sleeve 21 closely fitting over the downstream portion of the flame tube l. A circular series of apertures 28 are provided for the admission of primary combustion air to the space between the envelope 2 and the flame tube I, and further apertures 29 are provided in the sleeve corresponding to the apertures I! in the flame tube. It will be seen that due to differential thermal expansion between the sleeve 21 and the flame tube I, the apertures I! will be progressively blanked off as the temperature increases. The secondary air supply is thus restricted and a greater quantity of air is constrained to enter the primary combustion zone.
The proportions of the air stream entering the annular envelope 2, mixin air and coolant air are of course adjusted to suit the combustion requirements of the particular case under consideration.
We claim:
1. Combustion apparatus comprising an air casing having an air inlet, a flame tube within said air casing, a tubular sheath member enclosing and radially spaced from an upstream part of the flame tube to form therewith an annular passage, :the upstream end of said member (in relation to the flow of working fluid through the flame tube) being closed and the downstream end bein open and-forming with the flame tube an annular entry for a stream of primary air from the air casing to saidannular passage, means for injecting fuel intosaid annular passage to mix with the primary air, entry means connecting the annular passage to an upstream part of the interior of the flame tube, further entry means in the wall of the flame tube downstream of said sheath member for a stream of secondary air, and a valve located in and controlling the flow of one of said streams to vary the proportions of primary and secondary air.
2. Combustion apparatus according to claim 1 wherein said valve is operable, when the rate of delivery of fuel is varied, in a sense to maintain a substantially constant ratio between the quantitles of primary air and fuel.
3. Combustion apparatus according to claim 2 wherein said valve is operatively linked to an engine throttle.
4. Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, said entry comprising valve means controlling the flow of fuel/air mixture therethrough, and further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air.
5. Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of Working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, and further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air, and valve means controlling the flow of air/fuel mixture through the jacket, said valve means being actuated by differential thermal expansion 'be tween the flame tube and the enclosing structure.
6. Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein and entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, and further entry means including a valve in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air.
7. Combustion apparatus according to claim 6 wherein said valve is actuated by differential thermal expansion between the flame tube and the enclosing structure.
8. Combustion apparatus comprising an outer air casing, a flame tube within said air casing, a tubular sheath member closed at its upstream end (in relation to the flow of working fluid through the flame tube) and annularly enclosing the upstream part of the said flame tube, said sheath and flame tube together defining an annular jacket surrounding the latter, fuel injecting means introducing fuel into said jacket, means for leading air into said air casing, further means for dividing said air and delivering part thereof into said jacket as primary air to mix with the fuel therein, entry means connecting said jacket and flame tube whereby the fuel/air mixture is led into the latter, further entry means in the wall of the flame tube downstream of said jacket whereby a further part of the air is led into the flame tube as secondary air, and valve means controlling the flow through the jacket.
GEOFFREY J. POWTER. PETER LLOYD.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,052,588 J-anicki Feb. 11, 1913 1,733,792 Good Oct. 29, 1929 2,029,551 Baker Feb. 4, 1936 2,227,666 Noack Jan. 7, 1941 2,404,647 McCollum July 23, 1946 2,414,322 Mock Jan. 14, 1947 2,432,929 Parrish Dec. 16, 1947 2,458,497 Bailey Jan. 11, 1949 2,510,645 McMahan June 6, 1950 2,552,851 Gist May 15, 1951 FOREIGN PATENTS Number Country Date 6,816 Great Britain Apr. 1, 1901 386,908 Great Britain Jan. 26, 1933 603,918 Great Britain June 25, 1948 619,353 Great Britain Mar. 8, 1949 265,602 Germany Oct. 13, 1913 576,886 Germany May 20, 1933
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Cited By (55)

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US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2707989A (en) * 1952-08-26 1955-05-10 James William Edwards Burner for liquid
US2770096A (en) * 1952-09-15 1956-11-13 Phillips Petroleum Co Continuous combustion chamber with air flow and turbulence controlled by flame frontposition
US2837893A (en) * 1952-12-12 1958-06-10 Phillips Petroleum Co Automatic primary and secondary air flow regulation for gas turbine combustion chamber
US2941356A (en) * 1957-03-01 1960-06-21 United Aircraft Corp Variable pressure wave absorption for combustion chambers
US2952126A (en) * 1955-05-10 1960-09-13 Midland Ross Corp Combustion unit for supplying hot gas for jet aircraft
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US2974485A (en) * 1958-06-02 1961-03-14 Gen Electric Combustor for fluid fuels
DE1131947B (en) * 1959-03-28 1962-06-20 Maschf Augsburg Nuernberg Ag Combustion process for gas turbine combustion chambers and equipment for carrying out the process
US3055179A (en) * 1958-03-05 1962-09-25 Rolls Royce Gas turbine engine combustion equipment including multiple air inlets and fuel injection means
US3057158A (en) * 1959-01-29 1962-10-09 Rolls Royce Temperature responsive throttle for combustion chamber cooling air
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US6092590A (en) * 1996-05-03 2000-07-25 Daimlerchrysler Aerospace Airbus Gmbh Method and evaporator device for evaporating a low temperature liquid medium
US20040211186A1 (en) * 2003-04-28 2004-10-28 Stuttaford Peter J. Flamesheet combustor
US20050034444A1 (en) * 2003-08-16 2005-02-17 Sanders Noel A. Fuel injector
WO2008025525A1 (en) * 2006-08-30 2008-03-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method of controlling the combustion in a combustion chamber and combustion chamber device
US20100050653A1 (en) * 2008-09-04 2010-03-04 Kam-Kei Lam Combustor system and method of reducing combustion instability and/or emissions of a combustor system
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US20120297786A1 (en) * 2011-05-24 2012-11-29 General Electric Company System and method for flow control in gas turbine engine
US20140237999A1 (en) * 2013-02-27 2014-08-28 Tenneco Automotive Operating Company Inc. Exhaust Aftertreatment Burner With Preheated Combustion Air
US20140366542A1 (en) * 2006-06-26 2014-12-18 Joseph Michael Teets Fuel Air Premix Chamber For a Gas Turbine Engine
US20140366541A1 (en) * 2013-06-14 2014-12-18 General Electric Company Systems and apparatus relating to fuel injection in gas turbines
US8919127B2 (en) 2011-05-24 2014-12-30 General Electric Company System and method for flow control in gas turbine engine
US8925326B2 (en) 2011-05-24 2015-01-06 General Electric Company System and method for turbine combustor mounting assembly
US8959902B2 (en) 2013-02-27 2015-02-24 Tenneco Automotive Operating Company Inc. Exhaust treatment burner and mixer system
US8991163B2 (en) 2013-02-27 2015-03-31 Tenneco Automotive Operating Company Inc. Burner with air-assisted fuel nozzle and vaporizing ignition system
US9027332B2 (en) 2013-02-27 2015-05-12 Tenneco Automotive Operating Company Inc. Ion sensor with decoking heater
US20160186661A1 (en) * 2013-02-23 2016-06-30 Rolls-Royce Corporation Cooled cooling air taken directly from combustor dome
US9534525B2 (en) 2015-05-27 2017-01-03 Tenneco Automotive Operating Company Inc. Mixer assembly for exhaust aftertreatment system
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US10184664B2 (en) 2014-08-01 2019-01-22 Capstone Turbine Corporation Fuel injector for high flame speed fuel combustion
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IT202000022396A1 (en) * 2020-09-23 2022-03-23 Marelli Europe Spa HEATER DEVICE FOR AN EXHAUST SYSTEM OF AN INTERNAL COMBUSTION ENGINE
EP3356737B1 (en) * 2015-09-30 2022-05-25 IFP Energies nouvelles Thermodynamic cycle turbine with recuperator, for producing electrical energy

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US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2707989A (en) * 1952-08-26 1955-05-10 James William Edwards Burner for liquid
US2770096A (en) * 1952-09-15 1956-11-13 Phillips Petroleum Co Continuous combustion chamber with air flow and turbulence controlled by flame frontposition
US2837893A (en) * 1952-12-12 1958-06-10 Phillips Petroleum Co Automatic primary and secondary air flow regulation for gas turbine combustion chamber
US2952126A (en) * 1955-05-10 1960-09-13 Midland Ross Corp Combustion unit for supplying hot gas for jet aircraft
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US2941356A (en) * 1957-03-01 1960-06-21 United Aircraft Corp Variable pressure wave absorption for combustion chambers
US3055179A (en) * 1958-03-05 1962-09-25 Rolls Royce Gas turbine engine combustion equipment including multiple air inlets and fuel injection means
US2974485A (en) * 1958-06-02 1961-03-14 Gen Electric Combustor for fluid fuels
US3057158A (en) * 1959-01-29 1962-10-09 Rolls Royce Temperature responsive throttle for combustion chamber cooling air
DE1131947B (en) * 1959-03-28 1962-06-20 Maschf Augsburg Nuernberg Ag Combustion process for gas turbine combustion chambers and equipment for carrying out the process
US3078672A (en) * 1959-03-28 1963-02-26 Maschf Augsburg Nuernberg Ag Process and apparatus for operating a continuous or intermittent combustion engine
US3066727A (en) * 1959-06-09 1962-12-04 Ralph B Galvin Furnace involving temperature responsive compensation of combustion air
US3132683A (en) * 1960-06-07 1964-05-12 Bliss E W Co Aspirator burner
US3731484A (en) * 1967-11-10 1973-05-08 Lucas Ltd Joseph Apparatus for regulation of airflow to flame tubes for gas turbine engines
US3656297A (en) * 1968-05-13 1972-04-18 Rolls Royce Combustion chamber air inlet
US3765171A (en) * 1970-04-27 1973-10-16 Mtu Muenchen Gmbh Combustion chamber for gas turbine engines
DE2326302A1 (en) * 1972-05-25 1974-01-17 Ford Werke Ag DEVICE FOR CONTINUOUS FLAME BURNING A COMPRESSED AIR-FUEL MIXTURE
US3859786A (en) * 1972-05-25 1975-01-14 Ford Motor Co Combustor
US4078377A (en) * 1974-01-28 1978-03-14 Ford Motor Company Internally vaporizing low emission combustor
US3925002A (en) * 1974-11-11 1975-12-09 Gen Motors Corp Air preheating combustion apparatus
US4050238A (en) * 1975-03-14 1977-09-27 Daimler-Benz Aktiengesellschaft Film evaporating combustion chamber
US4150539A (en) * 1976-02-05 1979-04-24 Avco Corporation Low pollution combustor
US4099572A (en) * 1976-05-07 1978-07-11 Valentin Vasilievich Vasilenko Vapor-gas mixture generating installation for extinguishing underground fires
DE2620424A1 (en) * 1976-05-08 1977-11-17 Motoren Turbinen Union Variable geometry combustion chamber - has rotatable, axially movable outer casing and rotary slide valve, to vary secondary air
US4255122A (en) * 1977-02-23 1981-03-10 Forenade Fabriksverken Apparatus for combusting liquid, gaseous or powdered fuels
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
US4399652A (en) * 1981-03-30 1983-08-23 Curtiss-Wright Corporation Low BTU gas combustor
US4445570A (en) * 1982-02-25 1984-05-01 Retallick William B High pressure combustor having a catalytic air preheater
US5351474A (en) * 1991-12-18 1994-10-04 General Electric Company Combustor external air staging device
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
DE19523094A1 (en) * 1995-06-26 1997-01-02 Abb Management Ag Combustion chamber
US5832732A (en) * 1995-06-26 1998-11-10 Abb Research Ltd. Combustion chamber with air injector systems formed as a continuation of the combustor cooling passages
EP0780639A3 (en) * 1995-12-19 1999-04-07 DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung Combustion chamber
US6092590A (en) * 1996-05-03 2000-07-25 Daimlerchrysler Aerospace Airbus Gmbh Method and evaporator device for evaporating a low temperature liquid medium
US6263678B1 (en) 1996-05-03 2001-07-24 Daimlerchrysler Aerospace Airbus Gmbh Method of evaporating a low temperature liquid medium
US20040211186A1 (en) * 2003-04-28 2004-10-28 Stuttaford Peter J. Flamesheet combustor
US6935116B2 (en) * 2003-04-28 2005-08-30 Power Systems Mfg., Llc Flamesheet combustor
US20050034444A1 (en) * 2003-08-16 2005-02-17 Sanders Noel A. Fuel injector
US7200986B2 (en) * 2003-08-16 2007-04-10 Rolls-Royce Plc Fuel injector
US10422534B2 (en) * 2006-06-26 2019-09-24 Joseph Michael Teets Fuel air premix chamber for a gas turbine engine
US20140366542A1 (en) * 2006-06-26 2014-12-18 Joseph Michael Teets Fuel Air Premix Chamber For a Gas Turbine Engine
US20090205309A1 (en) * 2006-08-30 2009-08-20 Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. Method for controlling the combustion in a combustion chamber and combustion chamber device
WO2008025525A1 (en) * 2006-08-30 2008-03-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method of controlling the combustion in a combustion chamber and combustion chamber device
EP2161500A1 (en) 2008-09-04 2010-03-10 Siemens Aktiengesellschaft Combustor system and method of reducing combustion instability and/or emissions of a combustor system
US20100050653A1 (en) * 2008-09-04 2010-03-04 Kam-Kei Lam Combustor system and method of reducing combustion instability and/or emissions of a combustor system
EP2372245A1 (en) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Burner for stabilising the combustion of a gas turbine and method
EP2505921A3 (en) * 2011-03-28 2018-03-28 General Electric Company Combustor crossfire tube having purge holes
US8925326B2 (en) 2011-05-24 2015-01-06 General Electric Company System and method for turbine combustor mounting assembly
US8919127B2 (en) 2011-05-24 2014-12-30 General Electric Company System and method for flow control in gas turbine engine
US20120297786A1 (en) * 2011-05-24 2012-11-29 General Electric Company System and method for flow control in gas turbine engine
US8397514B2 (en) * 2011-05-24 2013-03-19 General Electric Company System and method for flow control in gas turbine engine
US20160186661A1 (en) * 2013-02-23 2016-06-30 Rolls-Royce Corporation Cooled cooling air taken directly from combustor dome
US10151243B2 (en) * 2013-02-23 2018-12-11 Rolls-Royce Corporation Cooled cooling air taken directly from combustor dome
US9027332B2 (en) 2013-02-27 2015-05-12 Tenneco Automotive Operating Company Inc. Ion sensor with decoking heater
US8991163B2 (en) 2013-02-27 2015-03-31 Tenneco Automotive Operating Company Inc. Burner with air-assisted fuel nozzle and vaporizing ignition system
US8959902B2 (en) 2013-02-27 2015-02-24 Tenneco Automotive Operating Company Inc. Exhaust treatment burner and mixer system
US9027331B2 (en) * 2013-02-27 2015-05-12 Tenneco Automotive Operating Company Inc. Exhaust aftertreatment burner with preheated combustion air
US20140237999A1 (en) * 2013-02-27 2014-08-28 Tenneco Automotive Operating Company Inc. Exhaust Aftertreatment Burner With Preheated Combustion Air
US20140366541A1 (en) * 2013-06-14 2014-12-18 General Electric Company Systems and apparatus relating to fuel injection in gas turbines
US10184664B2 (en) 2014-08-01 2019-01-22 Capstone Turbine Corporation Fuel injector for high flame speed fuel combustion
US9534525B2 (en) 2015-05-27 2017-01-03 Tenneco Automotive Operating Company Inc. Mixer assembly for exhaust aftertreatment system
EP3356737B1 (en) * 2015-09-30 2022-05-25 IFP Energies nouvelles Thermodynamic cycle turbine with recuperator, for producing electrical energy
EP3430316B1 (en) * 2016-03-18 2020-10-21 IFP Energies nouvelles Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy
US20190093569A1 (en) * 2017-09-25 2019-03-28 Delavan Inc. Electronic fuel control for gas turbine engines
US11053862B2 (en) * 2017-09-25 2021-07-06 Delavan Inc. Electronic fuel control for gas turbine engines
IT202000022396A1 (en) * 2020-09-23 2022-03-23 Marelli Europe Spa HEATER DEVICE FOR AN EXHAUST SYSTEM OF AN INTERNAL COMBUSTION ENGINE
CN114251161A (en) * 2020-09-23 2022-03-29 马瑞利欧洲公司 Heating device for exhaust system of internal combustion engine
EP3974626A1 (en) 2020-09-23 2022-03-30 Marelli Europe S.p.A. Heating device for an exhaust system of an internal combustion engine

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