U.S. patent number 3,869,865 [Application Number 05/372,514] was granted by the patent office on 1975-03-11 for devices for prevaporising liquid fuel.
This patent grant is currently assigned to Societe National D'Etude et de Construction de Moteurs D'Aviation. Invention is credited to Bernard Andre Cantaloube, Jacques Emile Jules Caruel, Armand Jean-Baptiste Lacroix, Herve Alain Quillevere.
United States Patent |
3,869,865 |
Lacroix , et al. |
March 11, 1975 |
DEVICES FOR PREVAPORISING LIQUID FUEL
Abstract
A device for prevaporising liquid fuel, designed for fitting to
a combustion system comprising a combustion chamber, a source of
liquid fuel and a source of gaseous comburrent agent, said device
being of the type which comprises, projecting into the combustion
chamber, a hollow structure incorporating a body and at least one
arm attached to said body and having at least one portion extending
transversely of the general direction of said body, the latter
comprising an entry portion which communicates with said sources of
liquid fuel and gaseous comburrent agent, and said arm having an
exit portion which opens into the combustion chamber and through
which, in operation, there is discharged a mixture of gaseous
comburrent agent and at least partially vaporised fuel, wherein
said hollow structure comprises, in a zone which incorporates the
transverse portion of said arm, a double-walled system constituted
by an internal wall and an external wall which together delimit two
separate passages, namely a central passage communicating both with
the source of gaseous comburrent agent and with the liquid fuel
source, and a peripheral passage communicating solely with the
source of gaseous agent.
Inventors: |
Lacroix; Armand Jean-Baptiste
(Itteville, FR), Quillevere; Herve Alain
(Issy-les-Moulineaux, FR), Cantaloube; Bernard Andre
(Chennevieres, FR), Caruel; Jacques Emile Jules
(Dammarie les Lys, FR) |
Assignee: |
Societe National D'Etude et de
Construction de Moteurs D'Aviation (Paris, FR)
|
Family
ID: |
9100723 |
Appl.
No.: |
05/372,514 |
Filed: |
June 22, 1973 |
Foreign Application Priority Data
|
|
|
|
|
Jun 23, 1972 [FR] |
|
|
72.22811 |
|
Current U.S.
Class: |
60/738;
239/132.3 |
Current CPC
Class: |
F23R
3/32 (20130101) |
Current International
Class: |
F23R
3/32 (20060101); F23R 3/30 (20060101); F02c
007/18 (); F02c 007/22 () |
Field of
Search: |
;60/39.71,39.74R,39.66,261 ;431/210,247,248 ;239/132-132.5 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Croyle; Carlton R.
Assistant Examiner: Garrett; Robert E.
Attorney, Agent or Firm: Daniel; William J.
Claims
We claim:
1. A device for prevaporising liquid fuel, designed for fitting to
a combustion system comprising a combustion chamber, a source of
liquid fuel and a source of gaseous comburrent agent, said device
being of the kind which comprises, projecting into the combustion
chamber, a hollow structure incorporating a body and at least one
arm attached to said body and having at least one portion extending
transversely of the general direction of said body, the latter
comprising an entry portion which communicates with said sources of
liquid fuel and gaseous comburrent agent, and said arm having an
exit portion which opens into the combustion chamber and through
which, in operation, there is discharged a mixture of gaseous
comburrent agent and at least partially vaporised fuel, in which
said hollow structure comprises, in a zone which incorporates the
transverse portion of said arm, a double-walled system comprising
an internal wall and an external wall which together delimit two
separate passages, namely a central passage communicating both with
the source of gaseous comburrent agent and with the liquid fuel
source, and a peripheral passage communicating solely with the
source of gaseous comburrent agent.
2. A prevaporisation device as claimed in claim 1, and further
comprising, arranged inside said peripheral passage at least in a
zone thereof situated along the transverse portion of said arm, at
least one blade or vane extending in a direction having a component
parallel to the general direction of flow in said peripheral
passage.
3. A prevaporisation device as claimed in claim 2, in which said
blade or vane is in contact with the external wall which delimits
said peripheral passage.
4. A prevaporisation device as claimed in claim 3, in which said
blade or vane is likewise in contact with the internal wall which
delimits said peripheral passage.
5. A prevaporisation device as claimed in claim 1, in which the
external wall which delimits said peripheral passage is pierced, at
least in a zone thereof situated along said arm, by a plurality of
sweat-pores through which a fraction of the gaseous comburrent
agent flow passing through said peripheral passage, can escape into
the combustion chamber.
6. A device for prevaporizing liquid fueld adapted to be fitted to
a combustion system comprising a combustion chamber, a source of
liquid fueld and a source of gaseous comburrent agent, said device
comprising, projecting into the combustion chamber, a hollow
structure incorporating a body and at least one arm attached to
said body and having at least one portion extending transversely of
the general direction of said body, said body comprising an entry
portion which communicates with said sources of liquid fuel and
gaseous comburrent agent, and said arm having an exit portion which
opens into the combustion chamber and through which, in operation,
there is discharged a mixture of gaseous comburrent agent and at
least partially vaporized fuel, in which said hollow structure
comprises, in a zone which incorporates the transverse portion of
said arm, a double-walled system comprising an internal wall and an
external wall which together delimit two separate passages, namely
a central passage communicating both with the source of gaseous
comburrent agent and with the liquid fueld source, and a peripheral
passage communicating solely with the source of gaseous comburrent
agent, said external wall being pierced by a plurality of
sweat-pores through which a fraction of the gaseous comburrent
agent flow passing through said peripheral passage can escape into
the combustion chamber, and at least one blade or vane arranged
inside said peripheral passage and extending in a direction having
a component parallel to the general direction of flow in said
peripheral passage.
Description
The present invention relates to a device for prevaporising liquid
fuel, designed for fitting to a combustion system comprising a
combustion chamber, a liquid fuel source and a source of gaseous
comburrent agent, said device being of the kind comprising,
projecting into said combustion chamber, a hollow structure
incorporating a body and at least one arm fixed to said body and
having at least one portion extending transversely of the general
direction of said body, the latter comprising an input portion
communicating with said sources of liquid fuel and gaseous
comburrent agent, and said arm having an exit portion which opens
into the combustion chamber and through which, in operation, there
is discharged a mixture of gaseous comburrent agent and at least
partially vaporised fuel.
The combustion system in question may, in particular, form part of
a gas turbine engine such as a turbojet engine.
One of the problems posed by the application of a hollow structure
of the aforedescribed kind, is that of protecting it against local
overheating, in particular of the zone of such arm or arms. This
structure is subjected to the extremely high temperatures which
prevail in the upstream part of the combustion chamber, and it can
also happen that inside said structure premature combustion of the
fuel flowing through it takes place.
It should be borne in mind in this context that a particularly
effective coolant for the hollow structure is constituted by fuel
in the course of prevaporisation, which is present inside said
structure.
However, it may happen that for one reason or another, the flow of
liquid fuel injected into the hollow structure, may be weaker than
intended. In particular, it may happen that the fuel injector
becomes partially or wholly obstructed. The direct consequence of
this situation is the absence, inside said structure, of an
adequate quantity of fuel in the process of vaporisation, and
therefore a lack of cooling of the structure.
As far as the risk of premature combustion of the fuel inside the
hollow structure is concerned, this happens when the richness of
the mixture of fuel and comburrent agent flowing through said
structure drops below a certain limit, i.e., in particular also in
the situation of partial obstruction of the injector.
The object of the present invention, in a general way, is to
diminish the risk of overheating of the hollow structure due to one
or the other of the two aforesaid causes.
To this end, in a prevaporisation device in accordance with the
invention, the hollow structure (which is of the kind defined
hereinbefore) comprises, in a zone which includes the transverse
portion of the arm, a double-walled system constituted by an
internal wall and an external wall together delimiting two separate
passages, namely a central passage communicating both with the
source of gaseous comburrent agent and with the liquid fuel source,
and a peripheral passage communicating solely with the source of
gaseous comburrent agent.
In accordance with a preferred embodiment, the prevaporisation
device of the invention comprises, arranged inside said peripheral
passage, at least within a zone of said passage which is located
along the transverse portion of said arm, at least one vane or
blade extending in a direction which has a component parallel to
the general direction of said peripheral passage.
In accordance with another embodiment of the invention, the
external wall which delimits the peripheral channel aforementioned,
is pierced, at least in the zone of said channel located along said
arm, by a plurality of sweat-pores through which a fraction of the
flow of gaseous comburrent agent passing through said peripheral
passage, can escape into the combustion chamber.
The arrangements hereinbefore described, make it possible to ensure
cooling of the hollow structure even in the event of partial or
possibly complete blockage of the fuel injector. In other words,
the peripheral passage, in all situations, passes a cooling gas
flow which makes it possible to dissipate towards the combustion
chamber the heat absorbed by the hollow structure. As will be
appreciated, the function of the blades or vanes is to promote the
transfer of said heat to the peripheral gas flow.
In addition, the risk of premature combustion in the hollow
structure is very much diminished by the fact that the richness of
the mixture of fuel and comburrent agent, in the central passage,
is radically increased as a consequence of the splitting of the
comburrent agent flow into two sub-flows only one of which actually
participates in combustion.
The description which now follows, given in relation to the
attached drawing, provided purely by way of non-limitative example,
will indicate how the invention may be put into effect.
FIG. 1 is an axial half-section through a combustion system
equipped with fuel prevaporisation devices;
FIG. 2 is a view in partial transverse section, on the line II--II
of FIG. 1, of said system;
FIG. 3 is a view on a larger scale, in section on the line III--III
of FIG. 2, of a fuel prevaporisation device of known kind;
FIG. 4 is a view similar to that of FIG. 3, showing an improved
prevaporisation device in accordance with the invention; and
FIG. 5 is a sectional view, taken on the line V--V, of part of the
prevaporisation device shown in FIG. 4.
In FIGS. 1 and 2, the general reference 7 has been utilised to
designate liquid fuel prevaporisation devices fitted to a
combustion system forming part, for example, of a gas turbine
engine such as turbojet engine.
This installation which is of the kind known per se, comprises for
example, a combustion chamber of axial X'-X, delimited by an
external casing 1a and an internal casing 1b which are
substantially coaxial with one another. These two casings together
define an annular space within which two walls 2a-2b, disposed
substantially coaxially vis-a-vis the two casings, delimit an
annular flame tube constituting the combustion space proper. This
latter is closed off at its upstream end, by an annular wall 3 or
dome, inside which there is disposed an annular supporting
structure 4. The dome 3 and the annular structure 4 are pierced by
holes 5-6 distributed uniformly about the axis X'-X of the chamber,
each hole 6 being arranged in extension of a hole 5. A
prevaporisation device 7 is assembled with a certain clearance, on
the axis of each of the holes 6. The combustion chamber is
connected at its upstream end to a source of comburrent agent such
as compressed air, schematically represented by a line 8. This air
circulates through the annular spaces defined respectively between
the casing 1a and the wall 2a, and the casing 1b and the wall 2b,
and enters the combustion space in the form of primary air, through
the holes 5, and in the form of secondary air for cooling and
dilution purposes, through holes 9a-9b, 10a-10b and 11a-11b. The
reference 20 signifies a source of liquid fuel.
Each prevaporisation device 7 comprises (see also FIG. 3) a hollow
structure projecting into the combustion chamber from a hole 6.
This hollow structure comprises a tubular body 12 coaxial with the
hole 6, and two arms 13, 14 fixed to said body, the assembly of the
body and the two arms presenting the appearance of a generally
T-shaped cane or the like.
The body 12 has an entry portion 12x communicating with the source
8 of gaseous comburrent agent, into which there also opens an
injector 17 supplied with liquid fuel from the source 20.
Each of the arms 13, 14 has a portion 13x, 14x standing
transversely to the general direction of the body 12, and an exit
portion 13y, 14y which opens into the combustion chamber and
through which, in operation, there is discharged a mixture of
gaseous comburrent agent and at least partially vaporised fuel. It
will be observed that each of the arms 13, 14 is bent so that its
exit portion 13y, 14y extends in a direction having a component
parallel to the general direction of the body 12.
The hole 6 has a larger cross-section than that of the body 12 in
order to enable the assembly, around said body, of a sleeve 18
which may possibly be integral with said body. Said sleeve, in
cooperation with the body 12, delimits an annular passage 19
through which direct admission into the combustion space, of a
certain fraction of the primary airflow, takes place.
In operation (see FIG. 3) the major fraction (marked by the
reference A) of the primary air flow, enters, at the same time as
the liquid fuel (marked by the reference C), the hollow structure
or cane 7, the walls of which, at their internal surfaces, are
subjected to the action of the flame so that the fuel vaporises.
The mixture of primary air and vaporised fuel (marked AC) if
discharged substantially axially through the exit portions 13y, 14y
of the arms 13, 14, in the reverse direction to the general
direction of the flow of combustion gases, which general direction
has been indicated in FIG. 1 by the arrow G. The smaller fraction
(marked by the reference "a") of the air flow entering at 19 around
the body 12, serves primarily to ensure a certain degree of thermal
insulation of the upstream portion of the body 12 of the hollow
structure 7.
The orifices 9a-9b, make it possible to produce two groups of
secondary air jets Fa-Fb which are substantially radially and
mutually oppositely directed. These jets meet one another in the
neighbourhood of the exit portions 13y, 14y of the arms 13, 14.
Part of their flow then recirculates towards the upstream part of
the chamber in order to produce, in the region adjacent the dome 3,
a turbulent zone which promotes ignition and maintenance of
combustion, whilst the other part of the flow passes directly
downstream in the direction of the arrow G, for example towards an
expansion turbine which has not been shown.
As mentioned hereinbefore, partial or total blockage of the fuel
injector 17 is dangerous for two reasons. On the one hand, in the
absence inside the hollow structure 7 of a sufficient quantity of
fuel in the course of vaporisation, this structure may be
insufficiently cooled. On the other hand, the richness of the
air-fuel mixture flowing through the hollow structure 7 may then
have diminished in such a proportion that premature ignition of the
fuel becomes possible, whilst the fuel is still inside the said
structure. In either case, the consequence is a risk of an
unacceptable degree of overheating of the hollow structure 7.
FIGS. 4 and 5 illustrate an example of a modified prevaporisation
device in accordance with the invention, the modification being
designed to reduce the risk of overheating referred to just
now.
This device, designated by the general reference 107, comprises a
hollow, bent, T-shaped structure, designed to project into the
combustion chamber. In the same way as the hollow structure 7
hereinbefore described, the hollow structure 107 comprises a body
112 and one or more arms 113, 114. The body 112 has an entry
portion 112x communicating with the source of gaseous comburrent
agent, and into which there opens a liquid fuel injector 117. Each
of the arms 113, 114 has a portion 113x, 114x, extending
transversely of the general direction of the body 112, and an exit
portion 113y, 114y which opens into the combustion chamber and
through which, in operation, there is discharged a mixture AC of
gaseous comburrent agent and at least partially vaporised fuel. The
exit portion 113y, 114y is preferably orientated in a direction
having a component parallel to the general direction of the body
112.
In accordance with the invention, the hollow structure 107
comprises at least in a zone which incorporates the transverse part
113x, 114x of the arm 113, 114 as well as a portion of the body
112, located near said transverse part, a double-walled system
constituted by an internal wall S and an external wall T, together
delimiting two separate passages, namely a central passage K.sub.1
and a peripheral passage K.sub.2. The two passages K.sub.1 and
K.sub.2 communicate with the source of gaseous comburrent agent,
but only the central passage K.sub.1 is supplied with liquid fuel
through the injector 117.
One or more blades or vanes 125 are arranged inside the peripheral
passage K.sub.2, at least in a zone thereof situated along the
transverse portion 113x, 114x of the arm 113, 114. As FIGS. 4 and 5
show, each of the blades or vanes 125 is in contact with the
internal S and external T walls which delimit the peripheral
passage K.sub.2 and extends in a direction having a component
parallel to the general direction of said peripheral passage. This
latter is thus sub-divided into at least two elementary passages
K.sub.21, K.sub.22 ... through which there flow in parallel
respective elementary flows of the gaseous comburrent agent.
The external wall T which delimits the peripheral passage K.sub.2
is pierced, at least in a zone of said passage disposed along the
arm 113, 114 by a plurality of sweat-pores 126 through which a
fraction of the gaseous comburrent agent flow passing through said
peripheral passage, can escape into the combustion chamber.
A sleeve 118, similar to that 18 hereinbefore described in relation
to FIG. 3, can furthermore be arranged around the external wall T
of the body 112 of the hollow structure, in a zone which comprises
at least the entry portion 112x of said body. Said sleeve 118 and
the external wall T thus together delimit a supplementary passage
119 having an entry end 119x communicating with the source of
gaseous comburrent agent, and an exit end 119y opening into the
combustion chamber.
In operation, the prevaporisation device 107 passes three coaxial
flows of gaseous comburrent agent, namely a central flow A.sub.1
passing through the central passage K.sub.1, a peripheral flow
A.sub.2 passing through the peripheral passage K.sub.2 and a
supplementary flow "a" passing through the supplementary passage
119. Only the central flow A.sub.1 contains fuel.
In the event that the injector 117 becomes blocked, the three
passages K.sub.1, K.sub.2, 119, continue to pass the gaseous
comburrent agent flows. The peripheral flow A.sub.2, a fraction s'
of which escapes through the sweat pores 126, thus makes it
possible to dissipate to the combustion chamber the heat absorbed
by the hollow structure, the transfer of this heat to the said flow
being accelerated by the presence of the blades or vanes 125.
The vent holes 126 furthermore ensure the development, in the
neighbourhood of the external wall of the hollow structure, of a
protective film of gaseous comburrent agent. Another protective
film is produced by the supplementary flow "a" of gaseous
comburrent agent, escaping from the supplementary passage 119.
As far as the risk of premature combustion of the fuel inside the
hollow structure is concerned, it will be seen that it is now very
much reduced because of the fact that the richness of the mixture
of fuel and comburrent agent is increased as a consequence of the
sub-division of the comburrent agent flow into two sub-flows only
one (the central flow A.sub.1) of which contains any fuel.
* * * * *