U.S. patent number 3,691,765 [Application Number 05/095,704] was granted by the patent office on 1972-09-19 for fuel injector for a gas turbine engine.
This patent grant is currently assigned to Rolls Royce Limited. Invention is credited to Denis Richard Carlisle.
United States Patent |
3,691,765 |
Carlisle |
September 19, 1972 |
FUEL INJECTOR FOR A GAS TURBINE ENGINE
Abstract
A fuel injector for a gas turbine engine is arranged to be
capable of supplying both liquid and gaseous fuels. The fuel
injector has a central member which has a plurality of liquid fuel
ducts having respective nozzles, a cowl surrounds the central
passage and defines therewith an annular gaseous fuel passage, a
baffle is mounted on the cowl downstream of the liquid fuel nozzles
and deflecting face is provided inside the cowl. The fuel emitted
from the nozzles is arranged to pass between the cowl and the
baffle and the fuel emitted from the central one of the nozzles is
arranged to impinge upon the deflecting face. A flow of high
pressure air is arranged to flow through a passage defined by the
shroud and the cowl and flow into the passage defined by the cowl
and the central member.
Inventors: |
Carlisle; Denis Richard
(Risley, EN) |
Assignee: |
Rolls Royce Limited (Derby,
EN)
|
Family
ID: |
10484761 |
Appl.
No.: |
05/095,704 |
Filed: |
December 7, 1970 |
Foreign Application Priority Data
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|
|
|
|
Dec 12, 1969 [GB] |
|
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59,965/69 |
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Current U.S.
Class: |
60/742; 239/524;
239/432 |
Current CPC
Class: |
F23D
17/002 (20130101); F23R 3/36 (20130101) |
Current International
Class: |
F23D
17/00 (20060101); F23R 3/28 (20060101); F23R
3/36 (20060101); F02g 001/00 () |
Field of
Search: |
;239/419.5,422,424,424.5,428,428.5,432,518,524
;60/39.74R,39.72R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Wood, Jr.; M. Henson
Assistant Examiner: Culp, Jr.; Thomas C.
Claims
What we claim is:
1. In a turbine engine having a fuel injector of the type including
a central member having a plurality of concentric nozzles, a shroud
mounted about a first portion of said central member and spaced
radially therefrom to define an annular fuel passage between said
central member and said shroud, means for supplying fuel to each of
said nozzles and said fuel passage, an annular cowl member mounted
about a second portion of said central member and spaced radially
therefrom the define an annular flow passage therebetween
downstream of said fuel passage, baffle means supported by said
cowl member and disposed downstream of said nozzles, said plurality
of concentric nozzles including at least one fuel nozzle having an
outlet means for spraying fuel at a predetermined angle into said
flow passage at least one other fuel nozzle having an outlet means
for spraying fuel into said flow passage, the improvement
comprising deflector means disposed coaxially with respect to said
nozzles and within said cowl for deflecting the spray from said one
other fuel nozzle so that fuel sprayed from said one other fuel
nozzle will enter said flow passage at an angle that is less than
said predetermined angle.
2. A fuel injector according to claim 1 in which the central member
has a central liquid fuel duct of relatively small cross-sectional
area terminating at a nozzle for use in pilot fuel combustion which
is concentrically surrounded by an annular liquid fuel duct of
relatively large cross-sectional area terminating at a nozzle for
use in main fuel combustion.
3. A fuel injector according to claim 2 in which the deflector
means is secured to the peripheral wall of the annular liquid fuel
nozzle.
4. A fuel injector according to claim 1 in which the deflector
means has an internal frusto-conical deflecting surface which is
coaxial with the nozzles and which diverges towards the baffle
means.
5. A fuel injector according to claim 1 in which said fuel passage
formed between the shroud member and said central member is a
gaseous fuel nozzle.
6. A fuel injector according to claim 1 which the baffle means
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.
7. A fuel injector according to claim 6 in which the member has a
plate secured to its downstream end which serves as a heat sink for
the prevention of carbon deposits on the member.
8. A fuel injector as claimed in claim 1 in which said cowl member
has a first portion which converges in the downstream direction and
a second portion downstream of said first portion which diverges in
the downstream direction.
Description
This invention concerns a fuel injector for a gas turbine
engine.
According to the present invention, there is provided a fuel
injector for a gas turbine engine comprising a central member
having a plurality of fuel ducts terminating in respective nozzles
and adapted to be connected to respective fuel supply means, a
shroud member mounted in a spaced relationship about the member and
forming an annular fuel passage therewith, a cowl member mounted in
spaced relationship about the central member and defining an
annular flow passage therewith, baffle means supported by the cowl
member and disposed downstream of the nozzles and deflector means
coaxial with and disposed within the cowl member, the fuel emitted
by the nozzles being arranged to pass between the cowl member and
the baffle means, the fuel emitted by the central one of said
nozzles being arranged to impinge upon the deflector means, and a
flow of high pressure being arranged to flow through a passage
defined by the shroud member and the cowl member into the passage
defined by the cowl member and the central member.
It will be appreciated that in a fuel injector according to the
present invention, the risk that a nozzle which is not in use at
any particular time will carbon up is reduced by reason of the fact
that the fuel from the remaining nozzle or nozzles is carried away
therefrom by the said flow of air, while the provision of the
deflector means widens the range of fuel spray angles produced by
the injector.
Preferably the outermost nozzle is a gaseous fuel nozzle, the other
nozzle or nozzles being liquid fuel nozzles.
There may be, in the central member a relatively small central
liquid fuel duct and nozzle for use in pilot fuel combustion which
are concentrically surrounded by a relatively large annular liquid
fuel duct and nozzle for use in main fuel combustion.
The deflector means is preferably secured to or formed integrally
with the radially outer wall of the annular liquid fuel nozzle, and
may have a frustoconical deflection surface which is coaxial with
the nozzles and which diverges towards the baffle means.
The baffle means preferably comprises a member having a
substantially conical surface the axis of which is common with the
axis of the nozzles and the apex of which is disposed towards the
nozzles.
Preferably the member has a plate secured to its downstream end
which plate serves as a heat sink for the prevention of carbon
deposits on the member.
The downstream end of the cowl member may be convergent in a
downstream direction at least a portion of the cowl member may be
convergent in a downstream direction.
Preferably the downstream end of the cowl is apertured to permit a
flow of high pressure air to pass therethrough and into the
passage.
The fuel supply means are preferably controllable to permit
simultaneous supply of gaseous fuel to the outermost nozzle and
liquid fuel to the other nozzle or nozzles.
There may be provided valve means associated with the gaseous fuel
nozzle for selectively connecting the latter to its respective fuel
supply means or to a source of high pressure air.
The invention also comprises a gas turbine engine provided with a
fuel injector as set forth above.
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 section, of a
gas turbine engine provided with a fuel injector according to the
present invention;
FIG. 2 is a broken away 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 12, combustion equipment 14,
and one or more turbines 16, the turbine exhaust gases being
directed to atmosphere through an exhaust duct 18 which may
terminate in a jet nozzle.
The combustion equipment 14 comprises a plurality of angularly
spaced apart flame tubes 20, each of the flame tubes being provided
at its upstream end with a fuel injector 22.
Each fuel injector 22 (FIG. 2) comprises a central body consisting
of a member 24 having a nut 26 secured to its downstream end the
central body and the nut in combination, retaining a nozzle member
28 in position. The nozzle member 28 has a relatively small,
centrally disposed nozzle 30 for the so-called "pilot" fuel, the
nozzle 30 being concentrically surrounded by a relatively large
annular nozzle 32 for the so-called "main" fuel which passes
through an annular aperture 33 the "pilot" and"main" fuels in this
preferred embodiment being liquid fuels. The radially outer wall of
the nozzle 32 has an axially extended portion 34 which is provided
with a frusto-conical deflecting surface 36 formed on its internal
surface. The nozzle 32 is itself concentrically surrounded by a
nozzle 38 which in operation emits gaseous fuel. The central member
24 is secured to a substantially L-shaped fuel feed arm 40 in which
are located respective fuel supply ducts 42, 44 and 46.
The nozzle 30 is constituted by three equi-angularly spaced apart
drillings 48 whose axes are inclined at an angle of about
70.degree. to the axis of the member 24 and intersect the
deflecting surface 36. The drillings 48 communicate at their
upstream ends with a pilot fuel passage 50 in the member 24 and
communicate at their downstream ends with the interior of a hollow
annular cowl 52. The axially extending limb of the fuel feed arm 40
has a shroud 54 brazed to its downstream end, and the shroud 54
supports by means of dowels 56 the cowl 52 so that the latter is
radially spaced from the nozzle 38. The cowl 52 carries three
equi-angularly spaced supporting members 58, each of which is
substantially Y-shaped in section and is secured, e.g. by brazing,
to a substantially conical baffle member 60 to support the latter.
The cowl 52 has an open upstream end 62 which defines with the
external surface the shroud 54 an annular air inlet. The cowl 52
converges from its upstream end 62 to an intermediate point 64
which is substantially co-planar with the downstream end of the
nozzle 30; the cowl 52 then diverges from the intermediate point 64
to an open downstream end 66 which is provided with throughgoing
apertures 68 which communicate with the flow passage 70 defined
between the central body 24 and nut 26 on the one hand and the
shroud 54 and the cowl 52 on the other hand.
The baffle member 60 is disposed inwardly of the downstream end 66
of the cowl 52, and the axis of its conical surface substantially
coincides with the axis of the nozzles 30, 32, 38, with the apex of
the cone being disposed towards the nozzle 30.
The downstream end of the baffle member 60 has a metallic heat
shield member 72 secured thereto. It will be appreciated that this
member 72 is in operation exposed to the internal temperature of
the flame tube and will thus transmit heat to the conical baffle
member 60 to a sufficient extent to prevent any accumulation of
carbon deposits thereon.
Air which has been compressed by the compressor or compressors 12
is in operation forced through the cowl 52.
The arrangement is such that the apex angle of the substantially
conical spray of fuel emitted by the nozzle 32 is determined by the
shape of the nozzle 32 and the necessity for clearing the baffle
member 60, and is typically about 90.degree.. This angle is very
suitable for normal running of the engine 10, but is too large to
provide good weak burning stability of good light-up and
light-round properties (i.e. weak extinction can easily occur, and
combustion does not start readily in a flame tube 20 and then
spread readily to the adjacent flame tubes 20). However, the
"pilot" fuel emitted from the drillings 48 impinges upon the
deflecting surface 36 and is deflected thereby into a substantially
conical spray having an apes angle of about 70.degree., which is
sufficient to clear the baffle member 60 owing to the radius of the
deflecting surface 36 and which substantially eliminates the above
mentioned weak burning and lighting problems.
The deflecting surface 36 on the portion 34 could, if desired, be
replaced by separate deflector means (not shown) suitably mounted
within the cowl 52.
The passage of gas fuel and/or liquid fuel through the cowl 52
takes place simultaneously with a flow of air through the cowl 52,
the said flow of air through the cowl 52 not only effecting
atomization of the fuel but also helping to ensure that the fuel is
burned away from the nozzles 30, 32, 38. Thus, carboning up of any
of the nozzles 30, 32, 38 which happens to be out of action at any
particular time is reduced. The baffle member 60 assists in
atomizing the fuel, the fuel and air being directed into a desired
direction between the baffle member 60 and the downstream end 66 of
the cowl 52.
The gas fuel passage 46 communicates at one end with the flow
passage 70, and at the other end with a gas manifold 74 (FIG. 1).
The liquid fuel ducts 42 and 44 respectively communicate with a
pilot fuel passage 76, via an annular chamber 78, and with the main
fuel passage 80. Both the liquid ducts 42, 44, communicate with a
liquid fuel manifold 82 (FIG. 1) so as to receive fuel
therefrom.
The manifolds 72, 82 are connected by respective lines 84, 86 to a
dual fuel control unit 88 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 22 is
operated on liquid fuel along, the problem arose that liquid fuel
sometimes splashed back into the gas fuel passage 70 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 gas fuel passage 70 of an injector of a relatively high
pressure combustion chamber and from there, via the gas fuel
manifold 82 into a relatively low pressure combustion chamber. This
is clearly undesireable.
These problems are overcome according to the illustrated embodiment
of this invention by the provision of a pair of shut-off valves 90,
92 (FIG. 1) connected to the gas fuel line 84. The valve 90, 92 are
so arranged that when one is open the other one is shut and
vice-versa. The valve 90 is disposed in a line 94 which connects
the gas fuel line 84 with a source of compressed air which in the
illustrated embodiment is tap-off from the outlet of the compressor
12. The valve 92 is upstream of the connection between the lines 84
and 94 and is disposed in the gas fuel line 84.
In operation, when liquid fuel only is being burnt, the gas fuel
supply is shut off by means of the valve 92, while the valve 90 is
opened to supply a continuous flow of compressed air from the line
94 to the gaseous fuel nozzle 38 by way of the line 84, the gas
manifold 74 and the passage 46.
* * * * *