JPH08261011A - Gas turbine device - Google Patents

Abstract

PURPOSE: To provide a thermal gas distributing manifold device which distributes thermal gas from a topping combustor symmetrically to a turbine inlet in a gas turbine device operated primarily on coal as its fuel. CONSTITUTION: Each topping combustor is connected to separate manifolds 52 and 54. Also both manifolds adjacent to each other in longitudinal arrangement are arranged in a casing 40 between the compressor part 2 and the turbine part 4 of a gas turbine, surround a rotor 12, and form troidal chambers 60 and 62. Then ducts 50 and 48 are extended to the downstream side from each manifold, and the duct of a front manifold passes through a rear manifold. Each duct is provided with annular duct outlet ports 74 and 72 which form an annular thermal gas flow path matching an annular inlet 95 to the turbine part. Each duct outlet port is arranged alternately so that thermal gas flows 36 and 35 from each topping combustor are distributed symmetrically to the periphery of the gas turbine inlet 95.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine device for generating shaft power, and more particularly to a plurality of external toppings for heating gas from a pressurized fluidized bed combustor (also abbreviated as PFBC). A hot gas manifold for a gas turbine system having a topping combustor.

[0002]

2. Description of the Related Art Systems based on gas turbines, which are highly efficient, have low equipment costs and short rise times, are particularly attractive to electric utilities as a means to generate electricity. However, conventionally, the fuels used to operate gas turbines have been limited to expensive, and sometimes surprisingly expensive fuels, primarily distilled oil and natural gas. On the other hand, since coal is easily available and low cost, great efforts have been made to develop a gas turbine device for power generation that can use coal as a main fuel. One system in which such efforts have primarily been directed is in systems for burning coal in a pressurized fluidized bed combustor.

In one example of the simplest gas turbine / PFBC power generation plant, a method of fluidizing a fluidized bed of PFBC by using ambient air compressed in a compressor section of a gas turbine and supplying combustion air to PFBC is used. is there. PF
After combustion in the BC, air having a high temperature and contaminated with combustion products and associated particulate matter is discharged from the PFBC. This air is then passed to a centrifuge where many of the particulate matter is removed. The air is then sent to the turbine section of the gas turbine where it expands, which produces useful shaft power. After expansion, the used air discharged from the turbine is released to the atmosphere.

However, the thermodynamic efficiency of such systems is poor. The reason is that in order to optimize the capture of sulfur contained in coal and to prevent harmful alkaline vapors from being carried into the turbine section, the temperature of the fluidized bed, and therefore the
This is because it is necessary to limit the temperature of the air flowing into the turbine section. In this regard, the turbine systems described above are in common use today and are significantly different from gas or liquid fuel-fired gas turbines that can operate at turbine inlet gas temperatures as high as 1425 ° C (2600 ° F). As is known in the art, increasing the temperature of the gas flowing into the turbine section can increase the output and efficiency of the gas turbine.

[0005] Therefore, in order to achieve maximum efficiency, the intention is to raise the temperature of the air exiting the PFBC to the temperature necessary to achieve maximum efficiency in the turbine, from the outside of the gas turbine and PFBC. It has been proposed to employ the provided combustor, ie a separate topping combustor. This topping combustor can burn with oil or natural gas, but in order to ensure maximum utilization of coal, a pyrolysis treatment operation (carbonizer or carbonizer) can be added to the system. Proposed. The carbonizer converts coal into low BTU gas and solid carbonaceous charcoal. Low BTU
The gas is burned in the topping combustor, while the charcoal is burned in the PFBC.

Further, it is desirable to utilize more than one topping combustor, for example, to keep the gas turbine running while repairing one of the topping combustors. However, in such a case, hot gas from the topping combustor that remains in service may cause the turbine section to avoid asymmetrical flow patterns due to the dormant topping combustor. It should be distributed as evenly as possible to the surroundings. Therefore, to distribute the hot gases from each of the plurality of topping combustors to the inlet of the turbine section of the gas turbine such that the hot gases from the individual combustors are distributed symmetrically around the inlet of the turbine. It is desirable to provide a manifold device of

[0007]

Accordingly, it is a general object of the present invention to provide for the inlet to the turbine section of a gas turbine such that the hot gases from each combustor are symmetrically distributed to the inlet of the turbine. It is to provide a manifold device for distributing hot gas from each of a plurality of topping combustors.

[0008]

SUMMARY OF THE INVENTION Briefly stated, the above and other objects of the present invention include a first combustor for combusting fuel in a compressed gas to produce a first hot gas flow, and a compressed gas in the compressed gas. Second combustor for combusting fuel to generate a second hot gas stream, a turbine having an inlet for receiving and expanding the first hot gas stream and the second hot gas stream, a first manifold and a second manifold And a gas turbine system including. here,
The first manifold receives the first hot gas stream from the first combustor and directs the first and second portions of the first hot gas stream to the first and second portions of the turbine inlet. It has a guide means. The second manifold also receives the second hot gas stream from the second combustor and directs the first and second portions of the second hot gas stream to the third and fourth portions of the turbine inlet. A third portion of the turbine inlet is disposed between the first portion and the second portion.

In one embodiment of the present invention, a gas turbine system includes a centrally located rotor and a shell containing the rotor. The first manifold and the second manifold surround the rotor and are housed in the shell, while the first combustor and the second combustor are located outside the shell. In this embodiment, the hot gas introduction means of the first manifold includes a first duct and a second duct that direct the first and second parts of the first hot gas stream to the first and second parts of the turbine inlet. And means for introducing hot gas in the second manifold include third and fourth ducts for directing the first and second portions of the second hot gas stream to the third and fourth portions of the turbine inlet. .

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT A preferred embodiment of the present invention will be described below with reference to the drawings. FIG. 1 shows a solid fuel gas turbine system. An oxygen-containing gas 6 such as ambient air flows into the compressor section 2 of the gas turbine 1 and is compressed.
A main portion 21 of the compressed air 20 generated by the compressor unit 2 is a pressurized fluidized bed combustor (also abbreviated as PFBC).
Sent to 8. The PFBC 8 consumes a solid fuel 18, which may be charcoal or charcoal generated by a carbonizer 9, as described below. The PF
BC8 includes a combustion chamber in which solid fuel is maintained in a pressurized fluidized bed to promote combustion.
Compressed air 20 fluidizes the fluidized bed and supplies the oxygen needed to combust the solid fuel. As a result of the combustion of fluidized solid fuel in compressed air, PFBC 8 produces compressed hot gas 32.

As already mentioned, the temperature of the hot gas 32 produced by the PFBC 8 is limited in order to optimize the capture of sulfur in the solid fuel and to prevent harmful alkaline vapors from entering the turbine section 4. It However, the power generated by the gas turbine 1 is proportional to the temperature drop in the turbine section 4, and the higher the temperature of the gas flowing into the gas turbine, the larger the power generated. Therefore, according to one important aspect of the present invention, the hot gas 32 produced in the PFBC 8, which is contaminated by combustion products, is sent to the centrifuge 10 and thereafter to the two external topping combustors 14 and 15 (the term “external” as used herein means external to the shell 40 of the gas turbine, as shown in FIG. 2). Gas fuel is supplied from the carbonizer 9 to these external topping combustors 14 and 15.

As shown in FIG. 1, a carbonizer 9 is fed with coal 11, which uses a pyrolysis process to produce a carbonaceous charcoal 18 and a hydrocarbon-based gaseous fuel 28, typically Converted to low BTU gas. In addition to the coal 11, it is necessary to supply high pressure oxygen to the carbonizer 9. This oxygen causes a portion 22 of the compressed air 20 discharged from the compressor unit 2 to be transferred to the booster compressor 13,
Then, it is obtained by extracting air into the carbonizer 9 from there. The low BTU gaseous fuel 28 produced by the carbonizer 9 is split into two streams of gaseous fuel 29 and 30, which streams are topping combustors 14 and 15.
Sent to each. In these combustors 14 and 15, the fuel will be combusted in the hot gas 32, which further raises its temperature. Topping combustor 1
Sufficient gas fuel 29 and 30 in the topping combustors 14 and 15 so that the gas streams 35 and 36 discharged from 4 and 15 are heated to the temperatures required to obtain the desired power output of the turbine. Is burned.

The hot gas streams 35 and 36 from the topping combustors 14 and 15 are then delivered to the turbine section 4 of the gas turbine 1 using the manifold arrangement of the present invention, as described below. In the turbine section 4, the hot gas flow 35
And 36 are expanded so that sufficient power is generated in the rotor 12 of the gas turbine to drive the generator 5. The expanded gas 7 is discharged to the atmosphere or sent to a heat recovery steam generator (not shown).

FIG. 2 is a sectional view of a part of the gas turbine 1 shown in FIG. As shown in FIG. 2, a substantially cylindrical casing 40 surrounds the central portion 3 of the gas turbine 1 arranged between the compressor portion 2 and the turbine portion 4. The compressor unit 2 is composed of a part of the rotor 12, around which a plurality of disks 90 and moving blades 91 are arranged in a row in the circumferential direction. Further, the compressor unit includes a plurality of vanes 104 arranged in a row extending in the circumferential direction between the rows of moving blades 91. The compressor section draws in ambient air 6 from its inlet and discharges the compressed air 20 via its conical diffuser 17 between its outlets.

Compressed air 20 discharged from the compressor section 2
Enters an annular chamber 42 defined by the casing 40 of the gas turbine. The chamber 42 encloses a part of the rotor 12, which is referred to as the torque tube, which connects the compressor part of the rotor to the turbine part of the rotor, whereby the compressor part 2 is connected to the turbine part 4. It is possible to drive by the power generated by. The rotor 12 is separated from the chamber 42 by a cylindrical housing 46.

In the casing 40, a chamber 42 is provided with a PFBC8.
Also, a pipe 24 is connected to establish an air flow communication with the carbonizer 9 so that the compressed air 20 can flow out of the chamber 42. After being heated in the PFBC 8 and in the topping combustors 14 and 15, P
A portion 21 of the compressed air 20 sent to the FBC 8 is returned to the chamber 42 in the form of hot gas streams 35 and 36. As shown in FIG. 2, hot gas streams 35 and 36 are delivered to chamber 42 by pipes 25 and 26 that pass through casing 40.

The pipe 26 directs the hot gas stream 35 from the topping combustor 14 to an inlet (reception means) 58 formed in the rear manifold 54. The pipe 25 also sends the hot gas stream 36 from the topping combustor 15 to an inlet (receiving means) 56 formed in the front manifold 52. still,
The front manifold 52 is arranged upstream of the rear manifold 54 in the axial direction. As shown in FIG. 2, manifolds 52 and 54 are located within a chamber 42 surrounded by casing 40.

The front manifold 52 is formed by radially extending circular front and rear end walls 96 and 97 and concentric inner and outer cylindrical walls 100 and 101 defining a toroidal chamber 60. Is made. The rear manifold 54 is formed by radially extending circular front and rear end walls 98 and 99 and concentric inner and outer cylindrical walls 102 and 103 to define a toroidal chamber 62. There is. Manifolds 52 and 54
Have centrally located holes 84 and 85, respectively, surrounding the compressor diffuser 17 and the rotor 12.

As shown in FIG. 3, the rear manifold 54
Has a substantially axially oriented duct 48 of a chamber extending from an opening 70 formed in the rear end wall 99 (in this example, three ducts are provided for each manifold). However, the present invention also
It is similarly applicable when using a larger number or a smaller number of ducts. ). The opening 70 is the duct 4
8 form the inlet for the duct 48 which places the 8 in flow communication with the toroidal chamber 62 and are evenly spaced apart in a circle. In this manner, the rear manifold 54 distributes the hot gas stream 35 received from the first topping combustor 14 into three parts, one for each duct 48. Three openings 82 are additionally formed in the rear end wall 99 and are evenly spaced along the same circle as the three duct inlets 70. In addition, the three openings 80 are three
It is formed in one front end wall 94 and is axially aligned with the hole 82 formed in the rear end wall 99. Each pair of holes 70 and 82 includes front and rear end walls 98 and 99.
They are connected by an axially oriented sleeve 64 extending therebetween.

Each of the ducts 48 has an arcuate outlet port 72 formed at its rear end. These ducts 48 are formed to transition from a circular inlet port 70 to an arcuate outlet port 72. Exit port 7
2 are evenly spaced along circles of slightly smaller diameter than the circles in which the inlets 70 of the ducts are spaced, so that these ducts 48, as clearly shown in FIG. Direction slightly inward in the radial direction when extending to the rear.

As shown in FIG. 4, the front manifold 52
Has three substantially axially oriented ducts 50 extending from openings 68 formed in its rear end wall 97. The opening 68 connects the duct 50 to the toroidal chamber 6
And an inlet port 70 of the rear manifold 54 is evenly distributed along a circle concentric with and spaced from the circle in which the inlet port 70 of the rear manifold 54 is spaced apart. Are spaced apart from each other.
In this manner, the front manifold 52 receives the hot gas flow 36 received from the second topping combustor 15 from each duct 50.
Distribute into 3 parts, one for each.

Each of the front manifold ducts 50 has an arcuate outlet port 74 formed at its rear end. These outlet ports 74 are concentric with the circle in which the rear manifold outlet ports 72 are spaced apart,
Moreover, they are evenly spaced along a circle having the same diameter as the circle, so that these ducts 50 likewise are slightly radially inward when they extend rearward in the axial direction. Each of the ducts 50 has an upstream cylindrical portion 7
6 and a downstream cylindrical portion 78, which, like the duct 48, are formed to transition from the cylindrical portion 76 to the arcuate outlet port 74. .

As shown in FIG. 5, manifolds 52 and 5
4, a cylindrical portion 76 of the front manifold 52 upstream of the duct 50 is coupled to penetrate a sleeve 64 in the rear manifold 54 to form a manifold assembly. As a result of the above construction, the ducts 48 and 50 are arranged in a circular alternating arrangement about the rotor 12,
Each duct is located between two adjacent ducts from the other manifold. Also, the lengths of the ducts 48 and 50 are such that all of the duct's outlet ports 72 and 74 lie in a common radially extending plane and, when combined, provide an annular exhaust or hot exhaust to the hot gas streams 35 and 36. It forms a discharge path.

As shown in FIG. 2, the outlet port 7 of the duct
The annular discharge passage formed by 2 and 74 is aligned with the shape and size of the annular inlet 95 of the turbine section 4,
It is arranged to direct the hot gas streams 35 and 36 directly to the turbine inlet 95. In this way, each of the duct outlet ports 72 ', 72 ", 72'", 74 ', 74 "and 74'" directs hot gas to the portion of the turbine inlet 95 immediately downstream thereof. When flowing into the turbine section 4, the hot gas streams 35 and 36 flow on the vanes 94 and the rotor blades 93 extending from the peripheral portion of the disk 92 to expand and are thereby cooled. Thus, power is generated in the rotor 12.

As shown in FIG. 5, manifolds 52 and 5
When assembling 4, the ducts 48 and 50 are assembled so as to alternate in the circumferential direction. As a result, the first front manifold duct outlet port 74 'is located between the first and second rear manifold duct outlet ports 72' and 72 ", and the second front manifold duct outlet port 7 '
4 "is the second and third rear manifold duct outlet port 7
2 ″ and 72 ′ ″, and a third manifold duct outlet port 74 ″ ″ is located between the first and third rear manifold duct outlet ports 72 ′ and 72 ′ ″.

Similarly, the first front manifold duct outlet 7
The portion of the turbine inlet 95 to which the hot gas flow is sent from 4'is the first and second rear manifold duct outlet ports 7
2'and 72 "are located between the portions of the turbine inlet that feed the hot gas flow, and the portion of the turbine inlet 95 that receives the hot gas flow from the second front manifold duct outlet port 74" is the second and third aft. Manifold duct outlet port 7
2 "and 72 '" are located between the portions of the turbine inlet that feed the hot gas stream, and a third front manifold duct outlet port 74 "' feeds the turbine inlet 95 that feeds the hot gas stream.
Is located between the portions of the turbine inlet where the first and third rear manifold duct outlet ports 72 'and 72'"feed the hot gas flow.

Thus, according to one important aspect of the present invention, the duct outlet port 72 of the rear manifold 54 and the duct outlet port 74 of the front manifold 52 are each
Independently of the other manifolds, each hot gas stream 35 and 36 is symmetrically distributed around the rotor 12 so that it is symmetrically distributed around the turbine inlet 95. Therefore, even if either of the topping combustors 14 or 15 is shut down and isolated from the system by the valve 16 shown in FIG. 1, the hot gas streams 35 or 3 from the other topping combustors are
The 6 are still distributed symmetrically around the turbine inlet 95, thereby avoiding harmful distortions of the hot gas flow in the turbine section 4.

Although the present invention has been described in the context of two topping combustors for a PFBC-based gas turbine system, the present invention is not limited to systems or systems using a greater number of topping combustors. It is also applicable to systems that use multiple combustors in other applications.
It is therefore noted that the invention can be embodied in other specific embodiments without departing from its spirit or essential attributes, and is not limited to the examples described above.

[Brief description of drawings]

FIG. 1 is a simplified diagram of a gas turbine system according to an embodiment of the invention comprising a PFBC (Pressurized Fluidized Bed Combustor), a dual topping combustor and a hot gas manifold system according to the invention.

FIG. 2 is a vertical cross-sectional view of a portion of the gas turbine shown in FIG. 1 in the vicinity of the hot gas manifold device.

FIG. 3 is a perspective view of the rear hot gas manifold shown in FIG.

4 is a perspective view of the front hot gas manifold shown in FIG. 2. FIG.

FIG. 5 is a perspective view showing the rear and front manifolds shown in FIGS. 3 and 4 in an assembled state.

[Explanation of symbols]

1 ... Gas turbine, 2 ... Compressor section, 4 ... Turbine section, 1
2 ... Rotor, 14, 15 ... Topping combustor, 28, 2
9, 30 ... Gas fuel, 32 ... Hot gas, 35, 36 ... Hot gas flow, 48, 50 ... Duct (guide means), 52, 54 ...
Manifold, 56 ... Manifold entrance (reception means),
58 ... Manifold entrance (reception means), 72, 74 ...
Duct outlet port, 95 ... Turbine inlet.

Claims (2)

[Claims] 1. A gas turbine system comprising: a) a first combustor for combusting fuel in compressed gas to generate a first hot gas flow; and b) combusting fuel in compressed gas for second. A second combustor generating a hot gas stream; c) a turbine having an inlet for receiving the first hot gas stream and the second hot gas stream for expansion therein; d) the first combustor to the second A receiving means for receiving a first hot gas stream and a first outlet port in flow communication between the first and second portions of the first hot gas stream with the first and second portions of the inlet of the turbine. And a first manifold having guide means leading to the second outlet port, and e) receiving means for receiving the second hot gas stream from the second combustor, a first portion and a second portion of the second hot gas stream. Two parts in flow communication with the third and fourth parts of the turbine inlet A second manifold in which the third outlet port is disposed between the first outlet port and the second outlet port, and a guide means for guiding the third outlet port and the fourth outlet port. Including a gas turbine device. 2. A gas turbine device comprising: a) a rotor, b) a plurality of combustors for generating hot gas, c) a turbine section for expanding the hot gas, and d) the combustor. Hot gas distribution means for distributing the hot gas from each of the turbine sections to the turbine section, the hot gas distribution means having a manifold for each of the combustors, each of the manifolds comprising: A plurality of ducts extending from the manifold, each duct having an outlet port formed therein, the duct outlet ports being arranged around the rotor in a circumferential array for each of the manifolds; The duct outlet ports are alternately arranged around the circumferential array such that the duct outlet ports from each manifold are located adjacent to the duct outlet ports from another manifold. That, the gas turbine system.