U.S. patent number 3,690,093 [Application Number 05/095,124] was granted by the patent office on 1972-09-12 for fuel injector for a gas turbine engine.
This patent grant is currently assigned to Rolls-Royce Limited. Invention is credited to Dennis Richard Carlisle.
United States Patent |
3,690,093 |
Carlisle |
September 12, 1972 |
FUEL INJECTOR FOR A GAS TURBINE ENGINE
Abstract
The invention comprises a gas turbine engine having a fuel
injector comprising a main body having therein a plurality of ducts
terminating in respective nozzles, fuel supply means for each of
said nozzles, a hollow annular cowl mounted in a radially spaced
relationship about the said main body so as to define therebetween
an air inlet, baffle means disposed downstream of said nozzles, and
valve means associated with a said duct for selectively connecting
the latter to its respective fuel supply means or to a source of
high pressure air, so that, in operation of the injector, the fuel,
or fuel and air, emitted by said nozzles passes between said cowl
and said baffle means, and simultaneously therewith a flow of high
pressure air passes from the compressor stage of the gas turbine
engine through said air inlet.
Inventors: |
Carlisle; Dennis Richard
(Derby, EN) |
Assignee: |
Rolls-Royce Limited (Derby,
Derbyshire, EN)
|
Family
ID: |
10484880 |
Appl.
No.: |
05/095,124 |
Filed: |
December 4, 1970 |
Foreign Application Priority Data
|
|
|
|
|
Dec 9, 1969 [GB] |
|
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60,035/69 |
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Current U.S.
Class: |
60/726; 60/742;
239/407; 60/39.463; 239/400 |
Current CPC
Class: |
F23R
3/36 (20130101) |
Current International
Class: |
F23R
3/28 (20060101); F23R 3/36 (20060101); F02c
003/22 () |
Field of
Search: |
;60/39.74R,39.27,39.46
;239/428,400,407 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Hart; Douglas
Claims
I claim:
1. A gas turbine engine having a compressor stage and a fuel
injector comprising a main body having therein a plurality of ducts
terminating in at least one liquid fuel nozzle and at least one
gaseous fuel nozzle, liquid fuel supply means for the liquid fuel
nozzle and gaseous fuel supply means for the gaseous fuel nozzle, a
hollow annular cowl mounted in radially spaced relationship about
said main body, said cowl and said main body being spaced to define
an air inlet, baffle means disposed downstream of said nozzles,
valve means associated with the duct which terminates in the
gaseous fuel nozzle, a source of high pressure air, means for
selectively connecting the gaseous fuel nozzle duct to the gaseous
fuel supply means or to said source of high pressure air so that
the liquid and high pressure air can flow from the liquid fuel
nozzle and the gaseous fuel nozzle respectively between said cowl
and said baffle means together with a flow of high pressure air
from said compressor stage of said engine which flows through said
air inlet.
2. A gas turbine engine as claimed in claim 1 in which the said
nozzles are concentric and the outermost nozzle is the gaseous fuel
nozzle.
3. A gas turbine engine as claimed in claim 2 wherein the fuel
supply means are controlled so as to permit simultaneous supply of
gaseous fuel to said outermost nozzle and liquid fuel to at least
the one liquid fuel nozzle.
4. A gas turbine engine as claimed in claim 1 in which in said main
body there is a relatively small diameter central liquid fuel duct
terminating in a nozzle for use in pilot fuel combustion which is
concentrically surrounded by a relatively large cross section
annular liquid fuel duct terminating in a nozzle for use in main
fuel combustion.
5. A gas turbine engine as claimed in claim 1 wherein the baffle
means is supported within said cowl and comprises a member having a
substantially conical surface the axis of which is common with the
axis of said nozzles and the apex of which is disposed towards said
nozzles.
6. A gas turbine engine as claimed in claim 5 wherein the said
member has a plate secured to its downstream end which plate serves
as a heat sink for the prevention of carbon deposits on said
member.
7. A gas turbine engine as claimed in claim 1 wherein the
downstream end of the cowl is divergent in a downstream
direction.
8. A gas turbine engine as claimed in claim 1 wherein at least a
portion of said cowl is convergent in a downstream direction.
9. A gas turbine engine as claimed in claim 1 wherein the
downstream end of said cowl is formed with an aperture to permit a
flow of high pressure air to pass therethrough and into a flow
passage between said cowl and said main body.
Description
This invention is concerned with a fuel injector for a gas turbine
engine.
According to the present invention, there is provided a gas turbine
engine having a fuel injector comprising a main body having therein
a plurality of ducts terminating in respective nozzles, fuel supply
means for each of said nozzles, a hollow annular cowl mounted in a
radially spaced relationship about the said main body so as to
define therebetween an air inlet, a baffle means disposed
downstream of said nozzles, and valve means associated with a said
duct for selectively connecting the latter to its respective fuel
supply means or to a source of high pressure air, so that, in
operation of the injector, the fuel, or fuel and air, emitted by
said nozzles passes between said cowl and said baffle means, and
simultaneously therewith a flow of high pressure air passes from
the compressor stage of the gas turbine engine through said air
inlet.
The fuel injector is of the kind which is the subject of British
Pat. application No. 59965/69.
It will be appreciated that in a gas turbine engine having a fuel
injector according to the present invention, the risk that a nozzle
which is connected to the duct associated with said valve means and
which is not in use at any particular time will carbon up is
reduced by reason of the fact that at such time a flow of air
through said duct will prevent entry thereinto of fuel from the
operative nozzle or nozzles.
Preferably the said nozzles are concentric and the outermost nozzle
is a gaseous fuel nozzle, the other nozzle or nozzles being liquid
fuel nozzles.
In a preferred embodiment, said valve means is associated with said
gaseous fuel nozzle only.
The fuel supply means are preferably controlled so as to permit
simultaneous supply of gaseous fuel to said outermost nozzle and
liquid fuel to the other nozzle(s).
There may be, in said central body, a relatively small diameter
central liquid fuel duct terminating in a nozzle for use in pilot
fuel combustion which is concentrically surrounded by a relatively
large cross-sectional area annular liquid fuel duct terminating in
a nozzle for use in main fuel combustion.
The baffle means is preferably supported by said cowl and comprises
a member having a substantially conical surface the axis of which
is common with the axis of said nozzles and the apex of which is
disposed towards said nozzles.
Preferably said member has a plate secured to its downstream end
which plate serves as a heat sink for the prevention of carbon
deposits on said member.
Optionally, the downstream end of the cowl is divergent in a
downstream direction.
Advantageously, at least a portion of said cowl is convergent in a
downstream direction.
Preferably, the downstream end of said cowl is apertured to permit
a flow of high pressure air to pass therethrough and into the air
inlet.
The invention is illustrated, merely by way of example, in the
accompanying drawings, in which:
FIG. 1 is a diagrammatic view, partly in broken-away longitudinal
section, of a gas turbine engine provided with a fuel injector
according to the present invention,
FIG. 2 is a broken away longitudinal sectional view on a larger
scale of the fuel injector shown in FIG. 1, and
FIG. 3 is a section taken on the line 3--3 of FIG. 2.
Referring to the drawings, a gas turbine engine 10 comprises in
flow series one or more compressors 11, combustion equipment 12,
and one or more turbines 13, the turbine exhaust gases being
directed to atmosphere through an exhaust duct 14 which may
terminate in a jet nozzle.
The combustion equipment 12 comprises a plurality of
circumferentially spaced apart flame tubes 15. Each of the flame
tubes 15 is provided at its upstream end with a fuel injector
16.
Each fuel injector 16 (FIG. 2) comprises a central body 17 having
secured thereto a nut 18 the downstream end of which is shaped to
form a relatively small, centrally disposed nozzle 20 for the
so-called "pilot" fuel, the nozzle 20 being concentrically
surrounded by a relatively large annular nozzle 21 formed by the
nut 18 for the so-called "main" fuel, the "pilot" and "main" fuels
in this preferred embodiment being liquid fuels. The central body
17 is secured centrally in one arm of a substantially L-shaped fuel
feed arm 19 in which are located three fuel supply ducts 43, 44 and
45. The left hand duct 43 (as seen in FIG. 2) communicates with a
pilot fuel passage 24 in the central nozzle 20 and the central fuel
supply duct 44 communicates with the main fuel passage 28 in the
large annular nozzle 21. The right hand duct 45 communicates with
an annular passage 35 formed between the central body 17 and a
shroud 22a brazed to the limb of the fuel feed arm 19 which is
substantially co-axial with the passages 28, 35 to form a nozzle 22
therewith. The central body 17 and the fuel feed arm 19 together
form said main body.
The downstream end of the nozzle 20 is provided with
circumferentially spaced drillings 23 which communicate at their
upstream ends with a pilot fuel passage 24 in the body 17 and which
communicate at their downstream ends with the interior of a hollow
annular cowl 25. The shroud 22a supports the cowl 25 by means of
dowels 29 so that the latter is radially spaced from the nozzle 22.
The cowl 25 carries three equi-angularly spaced supporting members
26. Each member is substantially Y-shaped in section and is
secured, e.g., by brazing, to a substantially conical baffle member
27 to support the latter. The cowl 25 has an open upstream portion
which defines, with the external surface of the shroud 22a an air
inlet 30. The cowl 25 converges from its upstream end 30 to an
intermediate point 31 which is substantially co-planar with the
downstream end of the nozzle 20; the cowl 25 then diverges from the
intermediate point 31 to an open downstream end 32 which is
provided with throughgoing apertures 33 which communicate with the
flow passage 35 defined between the central body 17 and nut 18 on
the one hand and the shroud 22a and the cowl 25 on the other
hand.
The baffle member 27 is disposed inwardly of the downstream end 32
of the cowl 25, and the axis of its conical surface substantially
coincides with the axis of the nozzles 20, 21, 22, with the apex of
the cone being disposed towards the nozzle 20.
The downstream end of the baffle member 27 has a metallic heat
shield member 36 secured thereto. It will be appreciated that this
member 36 is in operation exposed to the internal temperature of
the flame tube and will thus transmit heat to the conical baffle
member 27 to a sufficient extent to prevent any accumulation of
carbon deposits thereon.
Air which has been compressed by the compressor or compressors 11
is in operation forced through the inlet 30 in the cowl 25.
The passage of either gas or liquid fuel takes place through the
cowl 25 simultaneously with a flow of air, the flow of air through
the cowl 25 not only effecting atomization of the fuel but also
helping to ensure that the fuel is burned away from the nozzles 20,
21, 22. Thus carboning up of any of the nozzles 20, 21, 22 which
happens to be out of action at any particular time is reduced. The
baffle member 27 assists in atomizing the fuel, the fuel and air
being directed into a desired direction between the baffle member
27 and the downstream end 32 of the cowl 25.
The gas fuel passage 45 communicates at one end with the flow
passage 35, and at the other end with a gas manifold 52 (FIG. 1).
The liquid fuel ducts 43 and 44 respectively communicate with the
pilot fuel passage 24, via an annular chamber 55, and with the main
fuel passage 28. Both the liquid ducts 43, 44, communicate with a
liquid fuel manifold 56 (FIG. 1) so as to receive fuel
therefrom.
The manifolds 52, 56 are connected by respective lines 57, 58 to a
dual fuel flow control unit 60 which has means (not shown) for
enabling gaseous fuel and liquid fuel to be used either
simultaneously or separately from each other.
It has been found, however, that when the fuel injector 16 is
operated on liquid fuel alone, the problem arose that liquid fuel
sometimes splashed back into the annular passage 35 and hence to
the gas passage 45 wherein it spontaneously ignited. This
spontaneous ignition can, of course, damage the injector structure
and has to be prevented. Furthermore, in operation, the prevailing
pressures in the various combustion chambers of a given engine are
not always equal, and this gives rise to the possibility of hot
combustion products flowing back into the annular passage 35 of an
injector of a relatively high pressure combustion chamber and from
there, via the gas fuel manifold 52 into a relatively low pressure
combustion chamber. This is clearly undesirable.
These problems are overcome according to the illustrated embodiment
of this invention by the provision of a pair of shut-off valves 61,
62 (FIG. 1) connected to the gas fuel line 57. The valves 61, 62
are so arranged that when one is open, the other one is shut and
vice versa. The valve 61 is disposed in a line 63 which connects
the gas fuel line 57 with a source of compressed air which in the
illustrated embodiment is tap-off air from the outlet of the
compressor 11. The valve 62 is upstream of the connection between
the lines 57 and 63, and is disposed in the gas fuel line 57.
In operation, when liquid fuel only is being burnt, the gas fuel
supply is shut off by means of the valve 62, while the valve 61 is
opened to supply a continuous flow of compressed air from the line
63 to the gaseous fuel nozzle 22 by way of the line 57, the gas
manifold 52 and the passage 45.
* * * * *