U.S. patent number 3,905,192 [Application Number 05/501,739] was granted by the patent office on 1975-09-16 for combustor having staged premixing tubes.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Walter R. Kaminski, Robert M. Pierce, Philip W. Smith.
United States Patent |
3,905,192 |
Pierce , et al. |
September 16, 1975 |
Combustor having staged premixing tubes
Abstract
A gas turbine engine is shown having an annular burner with a
plurality of staged premixing tubes extending from the forward end
thereof. Each tube directs flow to the burner through two
concentric flow passages. A movable tube section is arranged to
direct all the air through both flow passages or just through one
passage. Fuel is directed into the staged premixing tube for mixing
with air flowing therethrough. Swirl vanes are provided in each of
the flow passages to provide for rotation of air passing
therethrough. A centerbody is positioned within the inner flow
passage providing a bluffbody to promote recirculatory flow in the
general region rearwardly of the centerbody. Cooling is provided
around the primary zone of the burner so as to provide a minimum of
cooling flow into the primary zone.
Inventors: |
Pierce; Robert M. (Tequesta,
FL), Smith; Philip W. (Lake Park, FL), Kaminski; Walter
R. (North Palm Beach, FL) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
23994832 |
Appl.
No.: |
05/501,739 |
Filed: |
August 29, 1974 |
Current U.S.
Class: |
60/737; 60/748;
239/402.5; 239/417; 60/39.23; 239/406; 60/749 |
Current CPC
Class: |
F23R
3/60 (20130101); F23R 3/50 (20130101); F23R
3/286 (20130101); F23R 3/30 (20130101); F23R
3/26 (20130101) |
Current International
Class: |
F23R
3/02 (20060101); F23R 3/30 (20060101); F23R
3/26 (20060101); F02C 007/22 () |
Field of
Search: |
;60/39.74R,39.74B,39.71
;239/401,402.5,406,416.5,417.3,417.5,417 ;431/354,355 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Freeh; William L.
Assistant Examiner: Garrett; Robert E.
Attorney, Agent or Firm: McCarthy; Jack N.
Government Interests
The invention disclosed herein was made in the course of or under a
contract with the Department of the Air Force.
Claims
We claim:
1. In combination, a staged premixing tube for directing a mixed
fuel-air flow into a burner, said staged premixing tube having an
outer tube for receiving fuel and air, said outer tube having an
inner tube located therein adjacent its rear end forming a first
inner passage and a second annular passage therearound, said outer
tube having a movable tube located therein forwardly of said inner
tube, said movable tube being movable between a first position
where it directs all of the flow in said outer tube through said
first inner passage to a second position where all of the flow is
directed through both of said first and second passages.
2. A combination as set forth in claim 1 wherein said outer tube is
formed having an inlet connected to a smaller center section by a
first inwardly tapered section, the forward end of said inner tube
being positioned adjacent said smaller center section, said movable
tube being formed having a large forward end with a second inwardly
tapered section and a smaller rear end, when said movable tube is
in its first position its rear end contacts the forward end of the
inner tube while its forward end contacts the first inwardly
tapered section of the outer tube.
3. A combination as set forth in claim 1 wherein a bluffbody is
positioned within said first inner passage forming an annular
passage.
4. A combination as set forth in claim 1 wherein first swirl vanes
are positioned in said first inner passage and second swirl vanes
are positioned in said second annular passage.
5. A combination as set forth in claim 3 wherein first swirl vanes
are positioned in said first inner annular passage and second swirl
vanes are positioned in said second annular passage.
6. A combination as set forth in claim 1 wherein a fuel nozzle
means directs fuel into said staged premixing tube, and a
compressor directs air into said staged premixing tube, and
actuating means are connected to said movable tube for moving
it.
7. A combination as set forth in claim 1 wherein a fuel nozzle
means extends into the forward end of said outer tube for directing
fuel into the staged premixing tube, said movable tube being
mounted for movement on said fuel nozzle means.
8. A combination as set forth in claim 7 wherein said fuel nozzle
means has a cylindrical surface thereon, said actuating means
having a sleeve which is axially movable on said cylindrical
surface of said fuel nozzle means.
9. In combination in a gas turbine engine, compressor means,
combustion means, turbine means, said combustion means having an
annular burner therein, fuel nozzle means, said burner having a
plurality of staged premixing tubes extending from the forward end
thereof, each staged premixing tube having an outer tube for
receiving fuel and air, each outer tube having an inner tube
located therein forming a first inner passage and a second annular
passage therearound, each outer tube having a movable tube located
therein forwardly of said inner tube, each movable tube being
movable between a first position where it directs all of the flow
entering its outer tube through the first inner passage to a second
position where all of the flow is directed through both of said
first and second passages.
10. A combination as set forth in claim 9 wherein said first
passage and second passage direct air into said burner with
counter-rotating swirling flows.
11. A combination as set forth in claim 9 wherein said annular
burner has a plurality of receptors extending forwardly thereof,
each receptor being positioned to receive a staged premixing tube,
each premixing tube being positioned in a receptor so that the rear
end thereof is positioned adjacent the forward end of the
burner.
12. A combination as set forth in claim 9 wherein means are
provided to move all of the movable tubes forwardly from their
first position when a predetermined fuel flow setting is
reached.
13. A combination as set forth in claim 9 wherein means are
provided to move each movable tube individually from its first
position to a second position around the annular burner.
14. A combination as set forth in claim 13 wherein said movable
tubes are moved between their first position and second position
sequentially around the burner.
Description
BACKGROUND OF THE INVENTION
This invention relates to the controlled formation of objectionable
or harmful exhaust emissions, such as unburned hydrocarbons, oxides
of nitrogen, and carbon monoxide, from a gas turbine engine burner
to maintain said objectionable or harmful exhaust emissions at an
acceptable level. A gas turbine engine burner ordinarily operates
over a wide range of primary zone equivalence ratios while it is
believed that the primary zone equivalence ratio should be
maintained within a narrow range. Prior devices have provided means
for varying the distribution of airflow within a burner and means
for providing atomization, premixing and substantial vaporization
but these means have not been set forth such as the device
described herein.
SUMMARY OF THE INVENTION
A primary object of the present invention is to provide a burner
with staged premixing tubes to control the formation of
objectionable or harmful exhaust emissions in a gas turbine engine
burner.
In accordance with the present invention, a staged premixing tube
is provided which varies the distribution of airflow within the
burner and provides fuel atomization, fuel-air premixing and
substantial vaporization of the fuel prior to injection into the
burner.
An object of this present invention is to provide a device which
will vary the distribution of airflow, and provide atomization,
premixing and substantial vaporization of the fuel with a minimum
of mechanical complexity, a high degree of reliability and a high
degree of premixing effectiveness.
In accordance with the present invention, all of the airflow
entering the primary zone of the burner is intimately premixed with
the fuel to entry into the burner over a range of different airflow
rates and different burner airflow distributions.
Another object of this invention is to provide a staged premixing
tube having two concentric annular flow passages which exit into
the burner; under conditions of low airflow only the smaller
diameter annular flow passage is used while under conditions of
high airflow both the smaller and larger diameter annular passages
are used.
Another object of the invention is to provide means for closing and
opening the larger diameter annular passage and at the same time
provide acceptable aerodynamic contours in both the inner and outer
passages so that high mixture velocities can be maintained in all
parts of the passages.
A further object of the invention is to provide a staged premixing
tube that allows the dissemination of fuel into the two annular
passages to be varied in terms of the relative portions of fuel
entering the inner and outer passages.
Another object of the invention is to provide a movable inner tube
of bellmouth cross section, said bellmouth piece, or tube, can
direct the total airflow and fuel flow into the smaller diameter
passage for low power engine operation and permit flow into both
passages for high power engine operation.
A further object of the invention is to provide a device for
variably apportioning the airflow entering a burner to the primary
combustion zone and to a secondary dilution zone to allow the
establishment of a plurality of engine burner airflow distribution
design points.
Another object of this invention is to provide a device wherein at
low power operation, a primary zone equivalence ratio is high
enough to support efficient combustion and provide an adequate
margin of operation above the lean blow out limit; and at high
power operation, the primary zone equivalence ratio is as low as
possible to avoid the formation of large concentration levels of
NO.sub.x.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a view of a gas turbine engine showing the location of
the burner having staged premixing tubes.
FIG. 2 is an enlarged sectional view of the combustion section
showing the burner and a staged premixing tube.
FIG. 3 is an enlarged view of a staged premixing tube in a position
for low power operation.
FIG. 4 is an enlarged view of a staged premixing tube in a position
for high power operation.
FIG. 5 is a view taken along the line 5--5 of FIG. 4.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to FIG. 1 as gas turbine power plant is shown indicated
generally by 1. The power plant has a compressor section 2, a
combustion section 4, a turbine section 6 and an exhaust section 8.
The combustion section 4 is comprised of an annular burner casing
10 with an annular burner 12 therein. A conventional fuel supply
and metering control 9 provides the desired fuel flow to an annular
manifold 11. Separate conduits 13 extend inwardly for a purpose to
be hereinafter described.
The annular burner 12 has a plurality of staged premixing tube 20
extending from the forward end thereof for delivering the
combustion airflow and fuel into the primary zone 22 of the burner
12. Annular flanges 24 and 26 extend from each side of the annular
opening 27 at the rear end of the annular burner 12 for positioning
the rear end of the burner 12 in the annular burner case 10. These
flanges 24 and 26 engage mating flanges 36 and 38 respectively
which project forwardly from the rear of the annular burner case 10
adjacent the turbine section 6. This positioning means places the
exit of the burner 10 at the entrance to the turbine section for
directing gas flow into turbine vanes 40.
The annular burner 12 is made having its forward portion which
encloses the primary zone 22 formed of double-walled construction
with a solid inner wall 25 and outer wall 29 having a plurality of
cooling holes 44 to provide for impingement cooling of wall 25. The
cooling air after it has completed its cooling function flows from
between the double-walled construction over the inner wall of the
remainder of the burner 12 so as not to enter the primary zone 22.
The rear part of the burner 12 which encloses the dilution zone has
its walls formed on conventional louver construction with dilution
openings 46 located adjacent the rear of the double-walled
construction and dilution holes 48 located rearwardly thereof
towards the annular openings 27 at the rear of the burner. A
cylindrical receptor 100 is mounted on the front of the annular
burner 12 where each staged premixing tube 20 is desired. While the
cylindrical receptor 100 is shown welded to the double-walled
construction of the annular burner 12, it is to be understood the
cylindrical receptor 100 may be connected by any other means. The
cylindrical receptor 100 has an annular flange 102 mounted
therearound for a purpose to be hereinafter described.
Air enters the annular burner case 10 of the combustion section 4
through the discharge passage 42 of the compressor f section 2
where it is distributed to various openings leading to the interior
of the annular burner 12. These openings include cooling holes 44,
dilution openings 46 and 48, and forward openings 50 of the staged
premixing tubes 20.
Each staged premixing tube 20 comprises three main parts, these are
(1) and outer tube 52, (2) a shorter inner tube 54 having a
centerbody 55, and (3) a movable bellmouth piece 56. The outer tube
52 has an enlarged inlet section 58 which is tapered inwardly as it
extends rearwardly to a reduced area center section 59. This inlet
section 58 directs incoming airflow from a forward opening 50 into
the premixing tube 20. The inner tube 54 is located in the rear end
portion of the outer tube 52 and with the centerbody 55 divides the
tube into two concentric flow passages 60 and 62. The inner tube 54
is supported within the outer tube 52 by swirl vanes 64. The
centerbody 55 is positioned in the inner tube 54 by swirl vanes 68.
The centerbody 55, while spacing the inner ends of the vanes 68,
also serve as an aerodynamic bluff-body, promoting recirculatory
flow in the general region just rearwardly of the centerbody. An
opening 57 extends through the center of the centerbody 55 to aid
in purging the region immediately adjacent to the centerbody of
combusting flow. The swirl vanes 64 and swirl vanes 68 are placed
in a manner so that airflow leaves the concentric flow passages 60
and 62 swirling in different directions. If desired, these vanes
can also be placed in a manner so that airflow leaves the flow
passages swirling in the same direction.
As shown, the inner tube 54 extends in length from the rear end of
the outer tube 52 forwardly to the reduced area center section 59.
This inner tube 54 tapers outwardly from its forward end to its
rearward end where it is attached by the swirl vanes 64 to the
outer tube 52. The center body 55 also tapers outwardly from its
forward end to its rearward end where it is supported within the
inner tube 54 by the swirl vanes 68. The cross-sectional area of
the flow passages 60 and 62 remains substantially constant
throughout their length.
The movable bellmouth piece 56 is shaped so that its rearward end
70 has a slidable engagement within the forward end of the inner
tube 54 when the bellmouth piece 56 is in its rearward position and
the forward edge contacts the inner surface of the outer tube 52
where it tapers inwardly to the reduced area center section 59 (see
FIG. 3). When the bellmouth piece 56 is in its forward position, it
is located so as to present as little interference as possible with
airflow passing thereby. The contour of the bellmouth piece 56 is
such that in its rearward position the forward edge coacts with the
inner wall of the inlet section 58 and the rearward end 70 coacts
with the forward end of the inner tube 54 to provide an acceptable
aerodynamic contour to direct inlet flow into only the smaller
diameter annular passage 62, and in its forward position it is
positioned within the forward part of the outer tube 52 so that
flow is directed smoothly into both of the concentric flow passages
60 and 62. The slidable engagement of the rearward end of the
bellmouth piece 56 with the forward end of the inner tube 54 is of
such a length that a small gap is permitted at A to permit airflow
therethrough before the bellmouth piece 56 disengages the inner
tube 54 as it moves forwardly.
Each staged premixing tube 20 has an annular flange 104 extending
outwardly from the midportion of the outer tube 52. This flange 104
is positioned on the outer tube 52 so that when the rearward end of
the staged premixing tube 20 reaches the end of the cylindrical
receptor 100 adjacent the inner part of the burner 12, it will
engage the cylindrical flange 102 of the cylindrical receptor 100.
These flanges are fixed together to retain the staged premixing
tube 20 in its proper operating position. The rearward end of the
staged premixing tube 20 has a plurality of radial projections 106
extending therefrom which guide the end of the staged premixing
tube 20 when it is being inserted in the cylindrical receptor 100
and provides for any flow of cooling air which may pass thereby. If
necessary, openings 108 can be provided in flange 104 to allow a
minimum of cooling air to enter the space between the outer tube 52
and cylindrical receptor 100.
As stated hereinbefore, fuel is delivered to an annular manifold 11
which distributes the fuel to separate conduits 13, each conduit
leading to a fuel atomizer, or nozzle, 72 of a staged premixing
tube. Each fuel nozzle is mounted in the inlet section 58 of the
outer tube 52, by means of three struts 74. The outer ends of the
struts 74 are fixed to the inner surface of the inlet section 58 of
the outer tube 52 and the inner ends are fixed to a cylindrical
housing 76 of the fuel nozzle 72. Each conduit 13 extends through
the wall of the discharge passage 42 of the compressor section 2
into a hollow strut 79. The conduit 13 then is angled in the strut
79 so that it extends to the front of the housing 76 of the nozzle
72 in an aligned manner which will be hereinafter described. The
conduit 13 is connected within the housing 76 to direct the flow of
fuel exit openings in the face of the nozzle 72. The conduit 13 can
be located in other positions to direct fuel to the nozzles 72. The
face of the fuel nozzle 72 is positioned adjacent the rear end of
the bellmouth piece 56, when the bellmouth piece 56 is in its
forward position so that fuel will be injected into both concentric
flow passages 60 and 62.
The fuel atomizer or nozzle 72 can have its design varied as long
as basic requirements for atomization and dispersion are met. While
one fuel nozzle 72 has been shown, dual nozzles can be used if
desired.
Actuating means 78 are provided for actuating the bellmouth piece
56 and include a sleeve 80 which has axial movement over the
cylindrical housing 76 of the nozzle 72. Slots 81 are provided for
the struts 74 which extend between the outer tube 52 and the fuel
nozzle 72. The forward end of the bellmouth piece 56 is connected
to the rearward end of the sleeve 80 by arms 82. A rack 84 is
located along the side of the sleeve 80 and is engaged by a pinion
gear 86 which is mounted on the end of a shaft 88 which extends to
the exterior of the annular burner case 10. A control device 90 is
connected to each shaft 88 for rotating its associated pinion gear
86 to translate its associated sleeve 80 and bellmouth piece 56. It
can be seen that rotation of the pinion gear 86 will axially move
the bellmouth piece 56 between its forward and rearward positions.
If additional means are desired to additionally support the sleeve
80 at its forward end, an arm can extend rearwardly from the rear
of a strut 79. This arm could be formed around a conduit 13
extending from a strut since the conduit 13 is positioned so that
the cylindrical sleeve 80 will be permitted axial movement
thereover. It is to be recognized that other known actuating means
can be used to translate the bellmouth piece 56.
While each staged premixing tube 20 has its bellmouth piece 56
separately actuated by a control device 90, the control devices can
be operated, for example, in any of the following manners: (1) all
of the control devices 90 can be interconnected so that the
bellmouth piece 56 of each staged premixer tube 20 directs flow
only into passage 62 for low power engine operation until a
predetermined higher power setting is reached and then the
bellmouth pieces 56 of all of the staged premixing tubes 20 can be
moved directly to an open position permitting flow to both flow
passages 60 and 62; (2) all of the control devices 90 can be
interconnected so that the bellmouth piece 56 of each staged
premixing tube will move from a low power setting by a
predetermined schedule until it reaches a predetermined higher
power setting and at that time the bellmouth pieces 56 can all move
directly to an open position; (3) all of the control devices 90 can
be interconnected so that the bellmouth pieces 56 of individual
staged premixing tubes 20 will be actuated in a predetermined
sequence around the circumference of the annular burner 12, when
one tube has been placed in its full open position then the
controlled device 90 of the next scheduled staged premixing tube 20
opens its bellmouth piece 56 and this continues until all of the
bellmouth pieces 56 are open, if a full power setting is
desired.
In the manner described in (3) above while each bellmouth piece 56
of each staged premixing tube 20 is operated in a predetermined
sequence, each tube can be operated such as set forth in manner (1)
or in manner (2). It is to be understood other types of operation
can be used depending on power requirements for any specific
engine.
* * * * *