U.S. patent number 3,830,620 [Application Number 05/227,788] was granted by the patent office on 1974-08-20 for gas burner for heat-recovery steam generator.
This patent grant is currently assigned to General Electric Company. Invention is credited to Frederick J. Martin.
United States Patent |
3,830,620 |
Martin |
August 20, 1974 |
GAS BURNER FOR HEAT-RECOVERY STEAM GENERATOR
Abstract
A gas burner comprising a straight main burner pipe with
imperforate horizontal wing baffles extending diametrically
thereform. The downstream side of the pipe is formed with a number
of fuel holes. Some fuel is fed directly toward an exhaust gas
recirculation pattern while the remaining fuel is distributed
laterally of the recirculation pattern toward an updraft of exhaust
gas. A second manifold pipe having a longitudinal row of fuel
distribution holes provides uniform fuel distribution in the main
pipe.
Inventors: |
Martin; Frederick J.
(Schenectady, NY) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
22854465 |
Appl.
No.: |
05/227,788 |
Filed: |
February 22, 1972 |
Current U.S.
Class: |
431/350; 60/739;
432/222; 60/749 |
Current CPC
Class: |
F23D
14/34 (20130101); F23D 14/045 (20130101); F23D
14/20 (20130101); F23D 14/70 (20130101); F23D
2900/21003 (20130101) |
Current International
Class: |
F23D
14/00 (20060101); F23D 14/46 (20060101); F23D
14/20 (20060101); F23D 14/70 (20060101); F23D
14/34 (20060101); F23D 14/04 (20060101); F23d
013/24 () |
Field of
Search: |
;263/19A ;431/350,180
;239/556-559 ;60/39.72R ;432/222 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Dority, Jr.; Carroll B.
Attorney, Agent or Firm: Ahern; John F. Mitchell; James
W.
Claims
What is claimed is:
1. A gas burner for heating an exhaust gas flow in a vitiated air
environment comprising:
an elongated gas burner pipe;
at least one pair of oppositely directed, imperforate, horizontal
wing baffles attached to said burner pipe, adapted to be
perpendicular to said exhaust gas flow for directing a portion of
said exhaust gas flow into a recirculation pattern downstream from
said burner pipe;
flame stabilization fuel ports on the downstream circumference of
the burner pipe for ejecting fuel into the recirculation pattern
forming a first combustible mixture; and,
main fuel ports on the downstream circumference of the burner pipe
for ejecting fuel laterally beyond the recirculation pattern into
the exhaust gas flow forming a second combustible mixture; said
flame stabilization ports and said main fuel ports symmetrical with
respect to the vertical centerline of the burner pipe; and, said
flame stabilization ports circumferentially nearer the vertical
centerline of the burner pipe and smaller in diameter than the main
fuel ports.
2. The gas burner as recited in claim 15 wherein a fuel
distribution manifold pipe, having spaced fuel holes along its
length, is positioned within the burner pipe for assuring uniform
distribution of gas fuel to the interior of the burner pipe.
3. The gas burner as recited in claim 15 wherein the flame
stabilization ports are displaced circumferentially on the order of
30.degree. from either side of the vertical centerline of the
pipe.
4. The gas burner as recited in claim 15 wherein the main fuel
ports are displaced circumferentially on the order of 60.degree.
from either side of the vertical centerline of the pipe.
5. The gas burner as recited in claim 15 wherein the width of each
burner wing may be on the order of one half the diameter of the
burner pipe.
6. A gas burner for heating an exhaust gas flow in a vitiated air
environment comprising:
an elongated cylindrical burner pipe adapted to be transversely
mounted with respect to the exhaust gas flow;
at least one pair of oppositely directed, coplanar, imperforate
horizontal wing baffles attached to said burner pipe and extending
radially of the burner pipe, adapted to be perpendicular to said
exhaust gas flow for directing a portion of said exhaust gas flow
into a recirculation pattern downstream from said burner pipe, said
baffles each having a width extending from the burner on the order
of one half the diameter of the burner; and,
at least two rows of fuel ports above said baffles and along the
length of said burner pipe, said rows of fuel ports symmetrical
with respect to the vertical centerline of said burner pipe and
having an included angle in the order of 60.degree. between said
rows.
Description
BACKGROUND OF THE INVENTION
This invention relates generally to gas burners for systems in
which the flow of air admitted to a combustion zone is considerably
in excess of the amount required to sustain combustion and the
object is to raise the temperature of the flow; and, in particular
this invention relates to a gas burner used to fire a heat recovery
steam generator in the exhaust duct of a gas turbine.
Gas turbine exhaust gases at 940.degree. F may first flow upward
through a bank of pre-evaporator tubes where the exhaust gas
temperature is reduced to about 540.degree. F. The gases then flow
upwardly, for heating, through a horizontal burner bed or grid
which comprises a number of spaced parallel main burner elements
arranged along the length of the burner bed. The gases then travel
vertically upward about 9 feet before passing through a bank of
finned boiler tubes. In this nine foot distance it is important to
burn the fuel gas from the burners completely and mix the hot
products with the excess air and turbine exhaust gas which bypasses
the flame, in order to achieve as uniform a temperature as possible
at the boiler tubes. The fuel gas flow to the burners is controlled
by regulating the fuel gas pressure to achieve an exhaust gas
temperature of 1,300.degree. F at the tubes. In addition to the
main burner elements, there are pilot burner elements transversely
mounted at opposite ends of the burner bed at right angles to the
main burner elements. The pilot burners are ignited first, burn
continuously, and eject a sheet of flame out over the downstream
sides of the main burner elements.
There are a variety of operating conditions to which the burner
must adjust, namely, the exhaust gases will normally be at
temperatures in the range of 500.degree. to 1,000.degree. F.,
flowing upwardly with velocities in the range of 10 to 100 feet per
second with oxygen contents in the range of 12 to 21 percent by
volume. The burner must therefore have a high "turn-down" ratio,
that is, a high ratio between maximum and minimum rates of
operation. Additionally, as fuel pressure is increased, in order to
meet increased heat requirements, the flame becomes unstable and
tends to burn off from the burner and upwardly toward the burner
tubes. This burn-off phenomena causes unequal heating of the boiler
tubes and can cause damage to the system.
Some prior art solutions to the burn-off phenomena are found in
patents to Yeo et al., specifically U.S. Pat. Reissue No. 25,626
issued July 28, 1964 and U.S. Pat. No. 3,178,161 issued Apr. 13,
1965. In the earlier issued patent, flame retention is provided by
a pair of perforated "gutter" wings fixed to a burner pipe. Air is
directed through the perforated wings and converges above the flame
and gas supply to form a canopy to ensure thorough mixing, heating
and combustion of the gas supply for all design ratio of operation.
The latter Yeo et al patent represents an improvement in that it
provided a "necked" wing burner to further contain the flames near
the burner pipes.
A somewhat different approach was taken in U.S. Pat. No. 3,574,507
to Kydd, issued Apr. 13, 1971 and assigned to the assignee of the
present invention. In that invention, a baffle was placed directly
above a high velocity fuel jet which deflected the fuel jet
laterally so as to provide a low velocity flame stabilizing
region.
SUMMARY OF THE INVENTION
A gas burner for firing a heat recovery steam generator in the
exhaust gas duct of a gas turbine. A burner pipe is formed with
diametrically opposed horizontal wing baffles; and, includes large
and small fuel jet openings respectively positioned and arranged at
greater and lesser circumferential distances from the burner pipe
vertical centerline. A part of the exhaust gas, due to the flat
wing baffles, is directed into a recirculation zone above and
downstream from the small fuel jet openings and establishes the
proper conditions for flame stability. THe large fuel jet openings
displaced further from the vertical centerline of the pipe, eject
fuel laterally beyond the recirculation zone whereupon the fuel is
caught in an updraft of exhaust gas and ignited by the stable
flame. The burner pipe may contain a concentrically mounted
manifold pipe with fuel distribution holes to assure uniform fuel
distribution within the main burner pipe.
It is, therefore, one object of the present invention to provide an
improved gas burner which will have a high "turn-down" ratio.
It is another object of the present invention to provide an
improved gas burner capable of sustaining flame stability under
relatively high fuel pressure conditions.
It is a further object of the present invention to provide an
improved gas burner which will provide more complete fuel
combustion within a specified combustion zone.
Other objects and advantages will become apparent from the
following description of the invention and the novel features will
be particularly pointed out hereinafter in the claims.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is an isometric view of a burner grid of the type which may
be incorporated into the exhaust duct of a gas turbine to supply
heat for a heat recovery steam generator.
FIG. 2 is an isometric view of the present invention removed from
the burner grid.
FIG. 3 is an end view of the present invention with arrows
indicating the flow of gas turbine exhaust gases.
DETAILED DESCRIPTION OF THE INVENTION
Illustrated in FIG. 1, a burner grid 11, of the type which may be
utilized in the exhaust stack of a gas turbine and used to heat
exhaust gases for firing a heat recovery steam generator or waste
heat boiler, is comprised of a rectangular frame 15 which is used
to support burner elements between two exhaust duct sections (not
shown). A flow distribution screen 19 may be used to form a porous
floor and is fixed to the rectangular frame by support beams 21
fixed traversely to opposite sides of the frame along the length
thereof.
At either end of the rectangular frame there may be a transversely
mounted pilot burner 25 including an ignitor 29. Each pilot burner
is connected at a gas inlet 27 to a gas supply (not shown) at one
end and may be capped at the opposed end so as to form a blind
burner pipe. The pilot burner may differ from the main gas burners
(according ot the present invention) in that it may be an ordinary
"gutter-wing" burner, according to the prior art, having a pair of
divergent wings 31 including air holes 35 and a row of fuel holes
39 on the burner pipe. Since the pilot burner supplies merely the
genesis of the burner conflagration, the fuel input here usually
remains constant at some relatively low value. The pilot burners
therefore are ignited to form a flame which is transversely
propagated at either end of the rectangular frame.
The main burners 41 form the basis of this invention, and are best
illustrated in FIGS. 1 and 2. The main burners may be
longitudinally oriented with respect to the burner grid and may be
supported by the transverse beams 21 as well as the rectangular
frame. The main burners are below or upstream of the pilot burners
and are perpendicular thereto Flame propagation in the main burners
is from either end of the rectangular support inwardly to
approximately the middle of the rectangular frame.
The main burners are each formed from a burner pipe 49 from which
extends a pair of horizontal wings 59. The wings extend
horizontally outward from the burner pipe and lie in a 180.degree.
plane with respect to one another and each wing lies at a
90.degree. angle with respect to the vertical centerline of the
burner pipe. The wings therefore lie perpendicular to the flow of
turbine exhaust gas. The wings are imperforate, but are provided
with periodic discontinuities or expansion slots 61 along the
burner length to accommodate thermal expansion and limit thermal
distortion. As an example, the width of each burner wing may be in
the order of one half the diameter of the burner pipe. Each burner
pipe includes a cap 65 to close one end of the burner forming
thusly another blind pipe.
The downstream (with respect to the flow of gas as shown in FIG. 3)
circumference of the burner pipe 49 includes a series of large and
small holes symmetrical with respect to the vertical centerline of
the pipe. These include main fuel ports 69 which are the larger
holes and flame stabilization ports 71 which are the smaller holes.
As an example, the ratio of the diameters between the main ports
and the stabilization ports may be in the order of 2 to 1. Furhter,
according to the present invention, the main fuel ports are
disposed in pairs, one on each side of the vertical centerline of
the burner pipe and each one port spaced a circumferential distance
of 60.degree. from the vertical centerline.
The flame stabilization holes or ports 71 (which are the smaller
holes) are spaced in pairs which alternate with the main fuel ports
along the burner length. The stabilization ports are each spaced 30
degrees from the vertical centerline on opposite sides of the
vertical centerline.
There is a smaller diameter manifold pipe 45, concentrically
mounted within the main burner pipe 49, and connected to a gas
inlet 51. This manifold pipe includes fuel distribution holes 55
which are formed along the top centerline of the pipe. These holes
are in effect gas distribution holes occurring about once per every
3 pairs of main burner holes which assure uniform gas distribution
into the burner pipe. The ratio of the mean diameter of the
manifold pipe to the mean diameter of the burner pipe may be in the
order of 3 to 4.
OPERATION OF THE INVENTION
Referring now to FIG. 1, the burner grid, which may be enlarged or
reduced in size according to the size of a gas turbine exhaust duct
and also according to heating requirements, receives an upward
draft of gas turbine exhaust gases having varying oxygen contents
and velocities. The pilot burners are fired by the ignitor and a
supply of gas through gas inlet 27. This spreads two sheets of
flame across the burner grid, one at each end. These flame sheets
are for igniting the main burners and produce relatively small
amounts of heat. Therefore, flame stability may be achieved by
adjusting the fuel gas pressure to a minimum pressure.
The main gas burners are supplied with gas fuel from the gas inlets
as shown. Gas fuel is fed into the main burner pipe from the
manifold pipe (FIG. 3) in order to uniformly distribute gas into
the burner pipe. Thereafter the gas is ejected from the main gas
ports and the flame stabilizing ports. The exhaust gases
immediately adjacent to the burner wings have a swirling motion
imparted to them because of the burner wings obstructing their
path. This causes an exhaust gas recirculation pattern above the
burner as indicated in FIG. 3. Fuel jets, from the flame
stabilization ports, are ejected into the recirculation pattern
forming a combustible mixture which is ignited by the pilot flame.
Because of the recirculation pattern, fuel jets may be completely
burned in a stable flame.
Meanwhile, fuel gas, issuing from the main gas ports, is ejected
laterally to either side of the recirculation zone, penetrating it,
until it is caught in an upward draft of turbine exhaust gases as
indicated in FIG. 3. This upward draft and the fuel carried with it
forms a combustible mixture peripheral to the stable flame which
now acts as a pilot flame for the main burner ports. Again, flame
stability is assured for all fuel pressures and complete combustion
of all fuel gases will occur.
Due to recirculating hot fuel gases above or downstream from the
burner together with the hot turbine exhaust gases, the fuel within
the burner pipe becomes progressively hotter as it passes down the
burner pipe. This affects the distribution of fuel flowing out
through the fuel ports and hence the size and stability of the
flame jets. To overcome this problem, the fuel distribution
manifold is inserted inside the main burner pipe as heretofore
described. This internal manifold is fed with fuel gas at higher
pressures up to 30 psig (or higher). A small number of fuel
distribution holes in the inner pipe distributes the gas uniformly
to the inside of the main burner pipe where the design pressure is
around 1 psig or less. In this way uniform flames along the length
of the burner are obtained.
While there has been described herein what is considered to be the
preferred embodiment of the invention, other modifications will
occur to those skilled in the art. The size and configuration of
the fuel holes are chosen to provide the flame stability and flame
spread required for the particular application. The size of the
fuel holes may vary according to their distance from the vertical
centerline of the burner pipe. It is intended to cover in the
appended claims all such modifications as fall within the true
spirit and scope of the invention.
* * * * *