JP2005113897A - Gas turbine and its operating method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine having a smaller size, high performance, simple construction and lower cost, and to provide its operating method. <P>SOLUTION: The gas turbine comprises a steam generation part 78 for generating saturated stream in a combustor 16 between an air compressor 12 and the turbine 14, an overheated stream generation part 104, and a steam-fuel mixture generation part 110. The overheated steam generation part converts the saturated steam into overheated steam which is mixed with fuel by a fuel injection part 106 to generate steam-fuel mixed gas to be supplied to burners 44, 46 of the combustor, thus achieving cleaned exhaust gas and improved heat efficiency. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a gas turbine, and more particularly, to a gas turbine that achieves thermal efficiency by preheating fuel and supplying it to a combustor, and a method for operating the gas turbine.

Conventionally, it has been proposed to improve the thermal efficiency of the gas turbine and reduce harmful exhaust gas by heating the fuel to be introduced into the combustor. In particular, from the viewpoint of air pollution prevention and countermeasures against global warming, an exhaust heat recovery steam generator (HRSG) is arranged on the exhaust side of the gas turbine to recover the exhaust heat energy and heat the fuel. Research to improve thermal efficiency and reduce fuel consumption, and to achieve low CO ₂ and low NO _X has become active.

  In US Pat. No. 4,932,204, an HRSG composed of a superheater, an evaporator and an economizer is provided on the exhaust side of the gas turbine, and an excessive water supply is circulated through the economizer to generate a heated water supply. It has been proposed to reduce the fuel efficiency of the gas turbine and improve the thermal efficiency of the gas turbine by circulating it through a vessel and preheating the fuel.

In US Pat. No. 5,095,693, a part of the compressed air of the air compressor is used as turbine cooling air, the fuel is preheated with the turbine cooling air, and HRSG is provided on the exhaust side of the gas turbine to generate water vapor. reducing the NO _X improves the thermal efficiency of the gas turbine has been proposed by a mixture of the preheated fuel and steam is supplied to the combustor Te.

  In US Pat. No. 5,357,746, US Pat. No. 5,826,430, US Pat. No. 6,065,280, US Pat. No. 6,269,626 and US Pat. No. 6,389,977, an HRSG is provided on the exhaust side of the gas turbine, and heated water or steam is generated by HRSG. In addition, it has been proposed to reduce the fuel efficiency of the gas turbine and improve the thermal efficiency of the gas turbine by circulating the heated feed water or steam through the heat exchanger to preheat the fuel.

In US Pat. No. 5,617,716, HRSG is provided on the exhaust side of the gas turbine, steam is generated by HRSG, the steam is circulated through a heat exchanger, and fuel is preheated. the fuel by mixing it is proposed to reduce the NO _X gas turbine.

  In US Pat. No. 5,806,298, an HRSG is provided on the exhaust side of the gas turbine, and steam is generated by the HRSG, and the steam is circulated through a heat exchanger to vaporize the fuel, thereby improving the thermal efficiency of the gas turbine. Proposed.

  US Pat. No. 5,845,481 proposes a structure in which a heat exchanger is housed in an exhaust tower and liquid fuel is circulated therein to heat the fuel.

  US Pat. No. 6,253,554 proposes that a part of the compressed air of an air compressor is used as turbine cooling air and the fuel is preheated with the turbine cooling air.

  However, in the gas turbines of US Pat. No. 4,932,204, US Pat. No. 5,095,693, US Pat. No. 5,357,746, US Pat. No. 5,826,430, US Pat. No. 6,065,280, US Pat. No. 6,269,626 and US Pat. Alternatively, since the HRSG for vaporization has a large structure and is composed of a large number of pipes and related valve members, the entire structure of the gas turbine becomes extremely complicated and large. In addition, since a large amount of exhaust heat energy leaks to the outside from these pipes and valves, the exhaust heat recovery efficiency is remarkably lowered, and it is difficult to effectively improve the thermal efficiency of the gas turbine.

Further, U.S. Patent No. 5617716 discloses a fuel gas supply method of the gas turbine so as to achieve a reduction of the NO _X by feeding heated vaporizing liquid fuel oil to a combustor of a gas turbine Yes. In this gas turbine, the liquid fuel oil is vaporized by supplying steam to the vaporization chamber using an exhaust heat recovery device disposed on the exhaust side of the gas turbine and an external steam generation source. The collector itself has a very large structure, and the manufacturing cost increases significantly. In addition, since an external steam generation source for vaporizing the fuel oil is further employed, the structure of the gas turbine becomes more and more complicated and the manufacturing cost increases. Moreover, since the fuel oil vaporization part is arrange | positioned independently from the combustor, while the vaporization part itself enlarges, a thermal energy leaks outside from this vaporization part, and it becomes a factor of thermal efficiency fall. Furthermore, between the liquid fuel pump and the vaporization section, a heat exchanger using a higher temperature lubricating oil and a heat exchanger using a higher temperature steam are connected in series to preheat the liquid fuel oil. Since this preheater requires complicated piping and a related valve member, the structure of the gas turbine becomes more complicated and causes further cost increase.

In the gas turbine of US Pat. No. 5,806,298, an exhaust heat recovery device (HRSG) is used to preheat or vaporize the fuel. As described above, the overall structure of the gas turbine is extremely complicated and large. To do. Furthermore, since a large amount of exhaust heat energy leaks to the outside from a large number of pipes and valves of the HRSG, the exhaust heat recovery efficiency is remarkably reduced, so the effect of improving the thermal efficiency of the gas turbine is low. In addition, in this gas turbine, since the vaporized fuel is mixed with the liquid fuel, the fuel itself introduced into the combustor is not sufficiently vaporized, and the liquid fuel is partially mixed. This liquid fuel locally forms a high-temperature portion of about 1600 ° C. in the combustion gas in the combustor, and has been a factor that NO _x increases remarkably.

  In the gas turbine of US Pat. No. 5,845,481 as well as the gas turbine described above, the heat exchanger installed in the exhaust tower has a complicated piping structure, which makes it difficult to improve the size and performance of the gas turbine and improve the thermal efficiency. It was.

  Further, in the gas turbine of US Pat. No. 6,253,554, the liquid fuel oil is heated using a heat exchanger disposed on the compressor side of the gas turbine. However, the heat exchanger itself has a very large structure and its manufacturing cost. Rises significantly. Moreover, heat energy leaks out from the heat exchanger itself, which causes a decrease in thermal efficiency. Therefore, it has been difficult to put into practical use a gas turbine that is compact, low-cost, and has high thermal efficiency.

Therefore, the present invention aims to reduce fuel consumption by obtaining a small size, high performance, compact size, low cost and high thermal efficiency, and also enables operation of lean turbine to realize low CO ₂ and low NO _X and operation of the gas turbine. It aims to provide a method.

  The present invention according to claim 1 is an air compressor in which a gas turbine supplies compressed air, a combustor that generates steam mixed power gas, and a turbine that generates power on an output shaft by expanding the steam mixed power gas. And a steam generating unit disposed in the combustor for generating saturated steam from feed water, and communicating with the steam generating unit and exchanging heat with the wall of the combustor to generate superheated steam from the saturated steam. A superheated steam generator, and a steam mixed fuel gas that is disposed along the outer periphery of the superheated steam generator on the downstream side of the superheated steam generator and generates a steam mixed fuel gas by bringing the superheated steam and fuel into contact with each other The gist includes a generator and a burner disposed in the combustor and configured to burn the steam mixed fuel gas and the compressed air to generate the steam mixed power gas.

According to the present invention of claim 1, saturated steam is generated using surplus heat of the combustor body, and superheated steam is generated while exchanging heat between the saturated steam and the combustor. By generating vapor mixed fuel gas by contacting with fuel, a uniform mixture of vapor mixed fuel gas and compressed air is generated in the combustor, and steam mixed power gas with a large mass is generated at a relatively low temperature. As a result, the thermal efficiency of the gas turbine is improved to improve the thermal efficiency of the gas turbine, and the NO _X emission amount is remarkably reduced and fuel consumption can be reduced. In particular, when a liquefied fuel such as LPG or LNG or a liquid fuel such as kerosene or heavy oil is used as the fuel, the complete gasification of these liquid fuels is promoted, so the gasified fuel and air in the combustor A uniform air-fuel mixture is generated to achieve complete combustion, and the emission of CO ₂ , HC, CO and other harmful gases can be greatly reduced. Furthermore, by eliminating the need for installing a large heat exchanger on the compressor side or on the exhaust side of the turbine, a compact and high performance gas turbine can be realized. In addition, since the combustor is heat-exchanged with saturated steam, melting damage due to the high temperature of the combustor is prevented, and the life of the combustor is significantly improved.

  According to a second aspect of the present invention, in the first aspect of the present invention, the water vapor generating section is disposed along the wall of the combustor to generate saturated steam, and the heat is supplied through a water supply valve. A water supply nozzle for injecting water into the replacement unit, and an operation parameter detector for detecting an operation parameter of the gas turbine and outputting a start signal, a warm-up operation signal, and a normal operation signal. In response, the controller includes a controller that controls the start-up operation, the warm-up operation, and the normal operation of the gas turbine, and the gist is that the controller opens the water supply valve after the warm-up operation ends.

  According to the second aspect of the present invention, before the gas turbine warm-up operation ends, the water supply valve is opened after the gas turbine warm-up operation is completed and water is supplied to the heat exchanger of the combustor to generate water vapor. In addition, it prevents water from flowing into the burner of the combustion chamber so that stable warm-up operation can be maintained. Furthermore, the arrangement of the heat exchanging unit in the combustor eliminates the need for an external large exhaust heat recovery steam generator (HRSG) that has been required in the past, and makes it possible to reduce the size and cost of the gas turbine.

  According to a third aspect of the present invention, there is provided the gas turbine according to the second aspect, wherein the steam-mixed fuel gas generating section is disposed on the outer peripheral side of the superheated steam generating section, and the superheated steam generating section A fuel injection unit communicating with the downstream side; a fuel injection nozzle for injecting fuel into the fuel injection unit; and a control valve for supplying the fuel to the fuel injection nozzle after completion of the warm-up operation by the controller It is to be prepared.

  According to the third aspect of the present invention, the partition portion of the steam mixed fuel gas generating section is disposed on the outer peripheral side of the superheated steam generating section so that complete vaporization can be achieved without causing fuel coking. It is a thing. Further, by providing a control valve for supplying the fuel to the fuel injection nozzle at the end of the warm-up operation of the gas turbine, it is possible to prevent malfunction of the gas turbine and ensure stable operation for a long period.

  According to a fourth aspect of the present invention, there is provided the gas turbine according to the third aspect, wherein the burner includes a pilot burner and a main burner, and the pilot burner and the main burner after the warm-up operation is finished by the controller. And a second control valve for supplying the vapor mixed fuel gas.

According to the fourth aspect of the present invention, since the steam mixed fuel gas is supplied not only to the main burner but also to the pilot burner after the warm-up operation of the gas turbine is completed, both the pilot burner and the main burner have low CO ₂ and low NOx. Is feasible. In particular, the conventional NOx pilot burners represent a significant proportion of the NO _X emissions in a gas turbine greatly reduced, there is a significant effect in the NO _X reduction of the entire gas turbine.

  The present invention according to claim 5 is a gas turbine operating method comprising: an air compressor that supplies compressed air; a combustor that generates steam mixed power gas; and an output shaft that expands the steam mixed power gas. A turbine for generating power, a superheated steam generator formed along a liner of the combustor, and a steam mixed fuel gas generated along a partition wall disposed on an outer peripheral side of the superheated steam generator A step of preparing a gas turbine comprising: a part; introducing a steam into the superheated steam generation part to generate superheated steam; and mixing the superheated steam and fuel in the steam mixed fuel gas generation part The present invention includes a step of generating a fuel gas; and a step of burning the vapor mixed fuel gas and the compressed air in the combustor to generate the vapor mixed power gas.

According to the fifth aspect of the present invention, there is no need for a large-sized heat exchanger composed of complicated piping and valves that cause a large structure and cost increase, and in a compact structure, the combustor does not cause coking. In addition, the fuel is heated by the excess heat, and overheated steam is generated to generate steam mixed fuel gas, thereby providing a gas turbine operating method capable of achieving low CO ₂ and low NO _X.

  According to a sixth aspect of the present invention, in the fifth aspect, the combustor further comprises a pilot burner and a main burner, and the steam is supplied to the pilot burner and the main burner after the warm-up operation of the gas turbine is completed. Supplying a mixed fuel gas.

According to the present invention of claim 6, not only the main burner, also the pilot burner that was capable of supplying the vapor fuel gas mixture can achieve significant reduction of the NO _X emissions main Barber and pilot burner In addition, it is possible to significantly improve the thermal efficiency of the gas turbine.

According to the gas turbine and the operation method of the gas turbine of the present invention, without using a conventional complicated and large exhaust heat recovery steam generator (HRSG) that causes a decrease in thermal efficiency, and without causing coking, Superheated steam is generated by using surplus heat of the combustor, while fuel is heated to generate steam mixed fuel gas, and a homogeneous mixture of steam mixed fuel gas and compressed air is generated in the combustion chamber This is a practical application of a small high-performance gas turbine that can realize low fuel consumption while improving thermal efficiency while reducing CO ₂ and NO _X.

  Hereinafter, preferred embodiments of the gas turbine of the present invention will be described with reference to the drawings.

  In FIG. 1, a gas turbine 10 includes an air compressor 12 that supplies compressed air, a turbine 14 that drives a load such as a generator 13 by expanding steam mixed power gas and generating power in an output shaft 14a, A combustor 16 disposed between the air compressor 12 and the turbine 14 to generate a homogeneous mixture of compressed air and steam mixed fuel gas to achieve lean combustion and generate steam mixed power gas Composed. In the present embodiment, the turbine 14 is shown as comprising a power turbine directly connected to the air compressor 12, but the turbine 14 is composed of a compressor turbine and a power turbine, and the compressor turbine is connected to the air compressor 12. A so-called two-shaft system may be employed in which the power turbine is connected to the output shaft.

  The combustor 16 includes an annular outer cylinder 18 and an annular inner cylinder 20 disposed concentrically therein. An outer liner 22 and an inner liner 24 are arranged concentrically in the annular space between the annular outer cylinder 18 and the annular inner cylinder 20 to constitute an annular combustion chamber 26. A tapered taper wall 26a is formed in the annular combustion chamber 26 along the rear portion, and a plurality of power gas injection nozzles 26b extending at equal intervals in the circumferential direction of the annular combustion chamber 26 further behind the end of the taper wall 26a. Is formed. An annular intermediate wall 28 extends concentrically between the annular inner cylinder 20 and the inner liner 24 to form an annular air passage 30. The outer liner 22 and the inner liner 24 are supported by the annular outer cylinder 18 and the annular intermediate wall portion 28 via annular front flanges 32 and 34, respectively.

  An annular header 36 is attached to the front edges of the annular outer cylinder 18 and the annular intermediate wall 28, and a plurality of burner holders 38 are attached at equal intervals in the circumferential direction of the annular header 36. A plurality of openings 36a and 36b are formed at equal intervals in the circumferential direction in the vicinity of the outer peripheral edge and the inner peripheral edge of the annular header 36, and the combustor receives compressed air from the air compressor 12 through the openings 36a and 36b. 16 is introduced. For this reason, annular air passages 40 and 42 are formed between the front portions of the annular front flanges 32 and 34 and the annular header 36, and these communicate with the aforementioned openings 36a and 36b. A plurality of communication ports 28 a are formed in the front portion of the annular intermediate wall portion 28 at equal intervals in the circumferential direction. Further, a plurality of air introduction small holes are formed at the front edges of the outer liner 22 and the inner liner 24, and the compressed air in the annular air passages 40 and 42 is introduced into the annular combustion chamber 26 through these small holes. .

  The burner holder 38 includes a pilot burner 44 supported at the center thereof, and a main burner 46 supported adjacent to the pilot burner 44. The pilot burner 44 includes a pilot fuel nozzle 48 supported by the burner holder 38 and a flame holding sleeve 50 supported by the burner holder 38 so as to be concentric with the pilot fuel nozzle 48. Pilot air passages 50a are formed in the front edge portion of the flame holding sleeve 50 at equal intervals in the circumferential direction. The pilot fuel nozzle 48 communicates with a pilot fuel pipe 52 supported by the burner holder 38, and pilot fuel is supplied to the pilot fuel pipe 52 via fuel control valves 54 and 55. A main fuel distribution path 38 a is formed in the burner holder 38, and the main burner 46 includes a plurality of main fuel nozzles 60 that are supported at equal intervals around the burner holder 38 and communicate with the main fuel distribution path 38 a. A main fuel supply pipe 62 is connected to the main fuel distribution path 38a, and main fuel is supplied to the main fuel supply pipe 62 through fuel control valves 56 and 57 as will be described later. After the warm-up operation of the gas turbine 10, the connection points of the fuel control valves 54 and 55 and the connection points of the fuel control valves 56 and 57 are used to supply the steam mixed fuel gas to the pilot burner 44 and the main burner 60, as will be described later. The 1st control valve 58 is connected to. In this embodiment, the main burner 46 is shown as comprising a plurality of main fuel nozzles 60 disposed around the pilot burner 44, but if necessary, near the front edges of the outer liner 22 and the inner liner 24. An auxiliary main burner may be further added.

  As shown in FIGS. 1 and 2, a rear plate 70 is fixed to the rear ends of the annular outer cylinder 18 and the annular inner cylinder 20 by welding or other means, and the annular partition wall 72 is spaced from the rear plate 70. Are fixed to the annular outer cylinder 18 and the annular inner cylinder 20. An annular channel member 74 is fixed to the annular partition wall 72 on the radially inner side of the plurality of power gas injection nozzles 26 b, and an annular steam passage 76 is formed on the inner side of the annular channel member 74. An annular heat exchange part 78 is arranged adjacent to a radial partition wall 78a extending in the radial direction between the annular outer cylinder 18 and the annular steam passage 76, and the annular heat exchange part 78 functions as a water vapor generating part. The water vapor generating part 78 includes a water supply injection chamber 82 having a water supply nozzle 80 adjacent to the radiation partition wall 78a, and an annular heat exchange passage 84 extending in the circumferential direction from the water supply injection chamber 82 in FIG. The water supply nozzle 80 is connected via a water supply control valve 81 to a water supply source (not shown) for supplying cold water, hot water or hot water, or a water vapor generation source (not shown).

  A plurality of baffle plates 86 are arranged radially in the middle of the power gas injection nozzle 26 b in the annular heat exchange passage 84, and the radially inner end of each baffle plate 86 is spaced from the outer periphery of the channel material 74 at a predetermined interval. And the flow path restricting portion 86a is formed. For this reason, the spray water injected from the water supply nozzle 80 passes through the high-temperature annular heat exchange passage 84 at the plurality of flow passage restriction portions 86a while passing through the annular heat-exchange passage 84, while the high-temperature power gas injection nozzle 26b. Saturated steam is generated by exchanging heat alternately with the outer wall. This saturated steam is recovered in the steam recovery chamber 88, a part of which is jetted into the outer annular passage 92 (see FIG. 1) through the first steam passage hole 90, and the remaining portion flows into the annular steam passage 76 through the communication hole 94. To do.

  The saturated steam S <b> 1 flowing into the annular steam passage 76 is jetted into the inner annular passage 98 (see FIG. 1) through the second steam passage hole 96. As shown in FIG. 1, radial fins 92 a and 92 b are radially arranged in the outer annular passage 92 so as to open alternately in the axial direction from the tapered portion 26 a on the outer diameter side, and flow into the outer annular passage 92 from the first steam passage hole 90. The saturated steam passes through the outer annular passage 92 extending in the circumferential direction and is introduced into the through hole 100a of the annular end flange 100 while cooling the tapered portion 26a on the outer diameter side of the combustion chamber 26. Similarly, radial fins 98a and 98b are radially arranged in the inner annular passage 98 so that the radial fins 98a and 98b are opened alternately in the axial direction from the tapered portion 26a on the inner diameter side, and the saturated steam flowing in from the second steam passage hole 96 is in the circumferential direction. The inner tapered passage 26a is introduced into the through hole 102a of the annular end flange 102 while cooling the tapered portion 26a on the inner diameter side. In this manner, the saturated steam in the outer annular passage 92 and the inner annular passage 98 is heated by exchanging heat with the outer diameter side and the inner diameter side tapered portion 26a.

  An annular partition wall 103 extends in the axial direction of the combustor 10 between the annular front flange 32 and the annular end flange 100, and a spiral rib 104 a is formed between the annular partition wall 103 and the outer liner 22. The superheated steam generation part 104 which consists of a spiral passage is formed, and its upstream part (rear part) communicates with the through hole 100a. A fuel injection section 106 is formed on the downstream side (front part) of the superheated steam generation section 104 adjacent to the plurality of steam injection ports 103a of the annular partition wall section 103. The fuel injection section 106 is fixedly supported by the outer cylinder 18. The fuel injection nozzle 108 is opened.

  Between the outer cylinder 18 and the annular partition wall 103, there is formed a steam mixed fuel gas generation unit 110 comprising a spiral passage formed by a spiral rib 110a. The upstream side and the downstream side of the steam mixed fuel gas generation unit 110 are Each is disposed adjacent to the annular front flange 32 and the annular end flange 100. The fuel injection nozzle 108 is connected to the fuel supply pipe 114 via the second control valve 112. A fuel outlet port 116 is disposed on the downstream side of the steam mixed fuel gas generation unit 110, and the fuel outlet port 116 is connected to the pilot fuel supply pipe 52 and the fuel control valves 55 and 57 through the first control valve 58 and the fuel control valves 55 and 57, respectively. Connected to the main fuel supply pipe 62.

  In FIG. 1, an annular steam passage 101 is further formed between the annular front flange 34 and the annular end flange 102, and the saturated steam introduced from the through hole 102 a of the annular end flange 102 removes excess heat from the inner liner 24. The recovered superheated steam is injected into the fuel chamber 26 through a plurality of steam injection nozzles 24 a formed on the inner liner 24. The annular steam passage 101 may have a spiral rib so that saturated steam exchanges heat with the inner liner 24 uniformly. On the other hand, the superheated steam recovered from the excess heat of the outer liner 22 is mixed with the vaporized fuel and injected from the burner to the combustion chamber 26. Further, the superheated steam generated by recovering the excess heat of the inner liner 24 enters the combustion chamber 26. By injecting, the thermal efficiency of the gas turbine is effectively improved.

  In FIG. 1, the fuel supplied to the fuel supply pipe 114 includes heavy oil, light oil, gasoline, kerosene, jet fuel, liquid hydrocarbon fuel such as methanol or ethanol, liquefied hydrocarbon fuel such as LNG and LPG, or natural gas. Including gas fuel.

  The gas turbine 10 further includes a controller 120 that controls start-up operation, warm-up operation, and normal operation. The controller 120 turns on / off a starter motor (not shown) of the gas turbine according to the operation of a main switch (not shown), ON / OFF of the first and second control valves 58, 112, a fuel control valve 54, 55, 56, 57 and a CPU that executes a program for controlling the opening degree of the water supply control valve 81, a RAM that temporarily stores a calculation result of the CPU, a ROM that stores a control program executed by the CPU, and an output circuit. The microcomputer (not shown) is configured as a main part.

  The CPU receives operation parameter signals such as an exhaust gas temperature detection signal, a load detection signal, and an axial speed signal from the exhaust gas temperature sensor 122, the load sensor 124, and the shaft speed sensor 126, which function as an operation parameter detector. If the shaft speed signal is a parameter related to the shaft speed, the rotational speed of the output shaft 14a or the output frequency of the generator 13 may be detected and the output signal may be used as the shaft speed signal. The controller 120 stores a temperature map for determining whether the operation is a start-up operation, a warm-up operation, or a normal operation. In response to the exhaust gas temperature detection signal, the temperature of the exhaust gas of the turbine 14 is a predetermined temperature. Compared with a threshold value corresponding to (for example, 650 to 680 ° C.), a warm-up operation end signal is output when the exhaust gas temperature detection signal becomes equal to or higher than the threshold value. The load sensor 124 is composed of, for example, a power detection sensor that detects the output power of the generator 13 and is used to determine the load state of the gas turbine 10 from the detected output power. Correspondingly, the controller 120 stores a load state determination map corresponding to light load, medium load, and high load of the gas turbine 10, and the fuel is determined according to the detected output power (gas turbine load). By controlling the opening of the control valves 54, 55, 56, and 57 and the opening of the water supply control valve 81, the flow rate of fuel and the amount of water supplied to the combustion chamber 26 are adjusted in accordance with the load of the gas turbine.

  Next, the operation of the gas turbine 10 will be described with reference to FIGS. When the gas turbine 10 is started, the start mode is selected by a command from the controller 120. In the start mode, a start motor (not shown) is started and the air compressor 12 is started. At startup, the controller 120 shuts off the first and second control valves 58 and 112 and opens only the fuel control valves 54 and 55. At this time, the fuel is injected into the combustion chamber 26 from the pilot fuel nozzle 48, mixed with the compressed air supplied from the flame holding sleeve 50, and then the pilot burner 44 is ignited by a spark plug (not shown). . Next, the ignition of the pilot burner 44 is detected by a frame sensor (not shown), and the controller 120 opens the fuel control valves 56 and 57. At this time, the main fuel is injected from the main fuel nozzle 60 into the combustion chamber 26 and mixed with the compressed air introduced from the front edges of the outer liner 22 and the inner liner 24 through the openings 36 a and 36 b of the annular header 36. Qi is generated and ignited from the pilot-burner 44. As a result, the gas turbine 10 is started and enters the warm-up operation mode. During the warm-up operation of the gas turbine 10, the controller 120 indicates that the output signal (that is, the operation parameter) of the exhaust gas temperature sensor 122 has reached a predetermined temperature after a predetermined time counted by a timer built in the controller 120 has elapsed. Judgment is made and a warm-up operation end signal is output. In response to the warm-up operation end signal, the water supply control valve 81 is opened, and the second control valve 112 is opened from the controller 120 after a predetermined time has elapsed since the water supply control valve 81 was opened. At this time, the spray water supplied from the water supply nozzle 80 becomes saturated steam by surplus heat of the combustor 16 while passing through the annular heat exchange passage 84 (see FIG. 2), and this saturated steam is converted into the steam recovery chamber 88 (see FIG. 2). 2). Next, the saturated steam flows into the outer annular passage 92 and the inner annular passage 98 through the first and second steam passage holes 90 and 96 (see FIG. 2), and then the passage holes 100a of the annular end flanges 100 and 102. , 102a are introduced into the superheated steam generator 104 and the annular steam passage 101, respectively, and the excess heat of the outer liner 22 and the inner liner 24 is recovered to become superheated steam. The superheated steam in the annular steam passage 101 is injected into the combustion chamber 26 through the steam injection nozzle 24a. On the other hand, after a predetermined time has elapsed after the water supply control valve 81 is opened, fuel is injected from the fuel injection nozzle 108 into the fuel injection unit 106 through the second control valve 112 opened from the controller 120. This fuel is mixed with superheated steam ejected from the steam injection port 103 a of the annular partition 103. The vapor mixed fuel gas generated in this way reaches the fuel outlet port 116 while being further uniformly mixed while passing through the vapor mixed fuel gas generating unit 110 formed of a spiral passage. After the second control valve 112 is opened by the controller 120 and a predetermined time has elapsed, the first control valve 58 is opened by the controller 120 and the fuel control valves 54 and 56 are shut off in synchronization with the first control valve 58. At this time, since the fuel control valves 55 and 57 are continuously maintained in the open state, the steam mixed fuel gas is supplied to the pilot burner 44 and the main burner 46, and a uniform mixture with the compressed air is generated in the combustion chamber 26. It is produced and burned to produce steam mixed power gas that is expanded in the turbine.

As is clear from the above, in this embodiment, the superheated steam is generated while effectively recovering the surplus heat of the combustor, and the steam mixed fuel gas is generated by the superheated steam. Therefore, a large exhaust heat recovery device (HRSG) is installed. As unnecessary, it is possible to realize a gas turbine having a small size, high performance, low cost, long life, high thermal efficiency, and low CO ₂ and low NO _x .

  Furthermore, in the present embodiment, the steam mixed fuel gas generating section is composed of a relatively low temperature partition provided on the outer peripheral side of the superheated steam generating section, so that the fuel is not exposed to high temperature and coking (carbonization) is performed. There is no waking. In addition, the surplus heat of the combustor liner is efficiently recovered by saturated steam, so that the combustor can be prevented from being damaged or deteriorated, the life of the combustor can be significantly extended, and maintenance is simplified. it can.

Further, in this embodiment, liquid fuel can be completely gasified, so that a homogeneous mixture on the lean side is generated in the combustion chamber, and complete combustion at about 1000 ° C. to 1200 ° C. is realized. It is also possible to save fuel and greatly reduce CO ₂ and NO _x . Moreover, since the gasification fuel containing superheated steam is introduced into the combustion chamber, it can be reduced more further NO _X.

  Further, in this embodiment, the superheated steam is generated by the inner liner of the combustion chamber and injected into the combustion chamber, so that the mass of the steam mixed power gas is increased and the performance of the gas turbine is dramatically improved. The For example, when the mixing ratio of superheated steam in the total power gas flow rate is 10% and 20%, the turbine output is remarkably increased to 150% and 220%, respectively.

  In this embodiment, the combustor 16 is illustrated as having an annular structure, but may be a can-type or can-annular structure.

Industrial applicability

  As described above, according to the present invention, it is possible to realize a small high-performance gas turbine having high thermal efficiency and low fuel consumption, clean exhaust gas, compact structure, and low cost. Therefore, such a gas turbine is expected to have a wide range of applications as a drive source for aircraft and land vehicles, and as a generator for industrial use and home use.

It is a schematic sectional drawing of the gas turbine by the Example of this invention. It is sectional drawing of the combustor of the gas turbine of the II-II line | wire of FIG.

Explanation of symbols

12 Air compressor 14 Turbine 16 Combustor 18 Outer cylinder 20 Inner cylinder 22 Outer liner 24 Inner liner 24a Steam injection nozzle 16 Combustor 26 Combustion chamber 36 Annular header 38 Burner holder 40, 42 Annular air passage 44 Pilot burner 46 Main burner 54 , 55, 56, 57 Fuel control valve 58 First control valve 78 Steam generation section 92, 98 Annular passage 101 Annular steam passage 103 Annular vaporization wall 103 a Steam injection port 104 Superheated steam generation part 106 Fuel injection part 110 Steam mixed fuel gas Generator 112 Second control valve 114 Fuel supply pipe 120 Controller 122 Exhaust gas temperature sensor 124 Load sensor 126 Shaft speed sensor

Claims (6)

  An air compressor that supplies compressed air, a combustor that generates steam mixed power gas, a turbine that expands the steam mixed power gas to generate power on an output shaft, and is disposed in the combustor and is saturated from feed water A steam generating unit that generates steam, a superheated steam generating unit that communicates with the steam generating unit and exchanges heat with the wall of the combustor to generate superheated steam from the saturated steam, and the superheated steam generating unit. A steam-mixed fuel gas generating unit that is disposed along the outer periphery of the superheated steam generating unit on the downstream side to generate a steam-mixed fuel gas by bringing the superheated steam and fuel into contact with each other; and the combustor. A gas turbine comprising: a burner that burns the steam mixed fuel gas and the compressed air to generate the steam mixed power gas.   2. The heat exchange unit according to claim 1, wherein the water vapor generation unit is disposed along a wall of the combustor to generate the saturated steam, and a water supply nozzle that injects water into the heat exchange unit via a water supply valve; And an operation parameter detector that detects an operation parameter of the gas turbine and outputs a start signal, a warm-up operation signal, and a normal operation signal, and in response to the signal, the gas turbine And a controller that controls a start-up operation, a warm-up operation, and a normal operation, and the controller opens the water supply valve after the warm-up operation ends.   3. The fuel gas generation unit according to claim 2, wherein the steam mixed fuel gas generation unit is disposed on the outer peripheral side of the superheated steam generation unit, the fuel injection unit communicates with the downstream side of the superheated steam generation unit, and the fuel injection unit. A gas turbine comprising: a fuel injection nozzle that injects fuel; and a first control valve that supplies the fuel to the fuel injection nozzle after completion of the warm-up operation by the controller.   4. The second burner according to claim 3, wherein the burner includes a pilot burner and a main burner, and is further opened after the warm-up operation by the controller to supply the steam mixed fuel gas to the pilot burner and the main burner. A gas turbine provided with a control valve.   A gas turbine operation method comprising: an air compressor that supplies compressed air; a combustor that generates steam mixed power gas; a turbine that expands the steam mixed power gas to generate power on an output shaft; A gas turbine comprising a superheated steam generator formed along a liner of a combustor and a steam mixed fuel gas generator formed along a partition wall disposed on an outer peripheral side of the superheated steam generator is prepared. Introducing steam into the superheated steam generator to generate superheated steam; mixing the superheated steam and fuel in the steam mixed fuel gas generator to generate steam mixed fuel gas; A method of operating a gas turbine comprising: a step of combusting a steam mixed fuel gas and the compressed air in the combustor to generate the steam mixed power gas.   6. The process according to claim 5, wherein the combustor further comprises a pilot burner and a main burner, and the steam mixed fuel gas is supplied to the pilot burner and the main burner after completion of the warm-up operation of the gas turbine. A method for operating a gas turbine.

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