JPH0626361A - Gas turbine - Google Patents

Gas turbine

Info

Publication number
JPH0626361A
JPH0626361A JP18095092A JP18095092A JPH0626361A JP H0626361 A JPH0626361 A JP H0626361A JP 18095092 A JP18095092 A JP 18095092A JP 18095092 A JP18095092 A JP 18095092A JP H0626361 A JPH0626361 A JP H0626361A
Authority
JP
Japan
Prior art keywords
turbine
heat exchanger
heat
exhaust
compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
JP18095092A
Other languages
Japanese (ja)
Inventor
Haruo Asami
春夫 阿佐美
Original Assignee
Kobe Steel Ltd
株式会社神戸製鋼所
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kobe Steel Ltd, 株式会社神戸製鋼所 filed Critical Kobe Steel Ltd
Priority to JP18095092A priority Critical patent/JPH0626361A/en
Publication of JPH0626361A publication Critical patent/JPH0626361A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE:To provide a gas turbine improving heat utilization at a heat exchanger without lowering fuel consumption efficiency and enabling the improvement of heat efficiency of a device and the reduction of NOx in exhaust gas. CONSTITUTION:A gas turbine is provided with a compressor 11, a turbine 13, a compressed gas supply passage 18 reaching the intake port 17 of the turbine 13 from the discharge port 14 of the compressor 11 through a heat exchanger 15 and a combustor 16, and an exhaust passage 20 passing the heat exchanger 15 from the exhaust port 19 of the turbine 13 so as to exchange heat with the compressed gas supply passage 18 inside the heat exchanger 15. This gas turbine is further provided with a water spray means l for spraying water to the compressed gas supply passage 18 part between the heat exchanger 15 and the discharge port 14.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine that reduces Nox in exhaust gas.

[0002]

2. Description of the Related Art Conventionally, a gas turbine shown in FIG. 2 is known, and a compressor 11 and a turbine 13 are provided.
In addition, the heat exchanger 1 from the discharge port 14 of the compressor 11
5, the compressed gas supply flow path 18 reaching the intake port 17 of the turbine 13 via the combustor 16, and the exhaust port 1 of the turbine 13.
9 through this heat exchanger 15
5, an exhaust passage 20 for exchanging heat with the compressed gas supply passage 18 is provided, and the combustor 16 has a fuel supply passage 2
1 is connected. Then, in the heat exchanger 15, the heat of the exhaust gas from the turbine 13 is used to compress the compressor 11
The fuel consumption in the combustor 16 required to heat the discharge air from the combustion chamber to the turbine inlet temperature is reduced, and the fuel consumption determined by the ratio of the output of the turbine 13 to the fuel consumption is reduced. It improves consumption efficiency.

As one case, in normal operation, at the inlet and outlet of the heat exchanger 15, points A (left side in FIG. 2), B (right side), and exhaust passage 20 of the compressed gas supply passage 18 are shown. The temperatures at point C (on the same right side), point D (on the same left side), and intake port 17 of turbine 13 are 180 ° C, 510 ° C, 560 ° C, and 230 ° in order from point A.
In the case of C, 810 ° C., if the room temperature is 15 ° C., the heat utilization rate is (560-230) / (560-15) = 0.606 ... (1) Become. Further, in order to make it easy to understand, when the specific heat of air is considered to be constant, the thermal efficiency η1 of the above apparatus is given by the following equation: η1 = {(810-560)-(180-15)} / (810-510) = 0 .283 (2)

On the other hand, the gas turbine shown in FIG. 3 is known in which, in addition to the above-mentioned utilization of exhaust heat, Nox in the exhaust gas is reduced and the turbine output is improved, which is common to the apparatus shown in FIG. The parts are shown with the same numbers. This device is provided with a compressed gas supply passage 1 from a discharge port 14 of a compressor 11 to an intake port 17 of a turbine 13.
The fuel supply passage 21 and the water injection passage 22 are connected to the combustor 16a provided in No. 8 so that water is injected into the combustion chamber in the combustor 16a.

[0005]

The thermal efficiency of the heat exchanger 15 in the apparatus shown in FIG. 2 described above increases as the difference in exhaust gas temperature between the inlet and outlet of the heat exchanger 15 increases.
However, since the discharge temperature of the compressor 11 is high, there is a problem that the exhaust gas temperature at the outlet of the heat exchanger 15 cannot be lowered sufficiently and the heat of the exhaust gas cannot be used efficiently. Further, if the temperature of the exhaust gas at the outlet is brought closer to the discharge temperature of the compressor 11 in order to use more heat of the exhaust gas,
The problem that the area of the heat transfer part of the heat exchanger 15 becomes very large arises.

On the other hand, in the case of the device shown in FIG. 3, since water is injected into the combustion chamber, there is a problem that the fuel consumption efficiency deteriorates. The present invention has been made to solve the above-mentioned conventional problems, and improves the heat utilization rate in a heat exchanger without lowering the fuel consumption efficiency, improves the output of a turbine, and improves the Nox in exhaust gas. It is intended to provide a gas turbine capable of reducing the above.

[0007]

In order to solve the above problems, the present invention provides a compressor, a turbine, a discharge port of the compressor, a heat exchanger, and a combustor to reach an intake port of the turbine. A compressed gas supply flow path, and an exhaust flow path that exits from the exhaust port of the turbine and exchanges heat with the compressed gas supply flow path in the heat exchanger via the heat exchanger. In the gas turbine described above, water spray means for spraying water is provided in the portion of the compressed gas supply passage between the heat exchanger and the discharge port.

[0008]

With the above-mentioned structure, the temperature of the air discharged from the compressor before entering the heat exchanger can be lowered until the evaporation of water does not occur.

[0009]

An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 shows a gas turbine according to the invention,
The apparatus is substantially the same as the apparatus shown in FIG. 2 except that a water spraying means 1 is newly provided. Corresponding parts are designated by the same reference numerals and description thereof will be omitted. This water spraying means 1
Sprays water into the inside of the compressed gas supply flow path 18 between the heat exchanger 15 and the discharge port 14, evaporates the water by the heat of the discharge air, and cools the discharge air by the heat of vaporization. It is what makes me.

In the case of this embodiment, the inlet portion of the heat exchanger 15,
The temperatures at points A and B of the compressed gas supply passage 18 at the outlet, points C and D of the exhaust passage 20 and the intake port 17 of the turbine 13 are 80 ° in order from the point A.
C, 510 ° C, 560 ° C, 130 ° C, 810 °
C or a value close to this. The heat utilization rate is (560-130) / (560-15) = 0.789 (3).

The thermal efficiency η2 of the apparatus is η2 = {(810-560)-(180-15) .0.954.0.964} / (810-510) = 0.327 (4) , In the case of the device shown in FIG. 2 (0.606,
0.283), and Nox in exhaust gas is also reduced by water spray. It should be noted that 0.954 and 0.964 in the formula before the formula (4) are obtained from the following formula. 0.954 = air flow rate / exhaust gas flow rate (including water content) (5) 0.964 = air specific heat / exhaust gas specific heat (including water content) (6)

[0012]

As is apparent from the above description, according to the present invention, the compressor, the turbine, and the compression from the discharge port of the compressor to the intake port of the turbine via the heat exchanger and the combustor. A gas supply flow path and an exhaust flow path that exits from the exhaust port of the turbine and exchanges heat with the compressed gas supply flow path in the heat exchanger via the heat exchanger are provided. In the gas turbine, water spray means for spraying water is provided in the compressed gas supply passage between the heat exchanger and the discharge port. For this reason, the temperature of the air discharged from the compressor before entering the heat exchanger can be lowered until water evaporation does not occur, and the heat utilization rate in the heat exchanger can be reduced without reducing the fuel consumption efficiency. And the thermal efficiency of the device can be improved, and along with this, Nox in the exhaust gas can be reduced.

[Brief description of drawings]

FIG. 1 is an overall configuration diagram of a gas turbine according to the present invention.

FIG. 2 is an overall configuration diagram of a conventional gas turbine regeneration cycle.

FIG. 3 is an overall configuration diagram of a conventional gas turbine simple cycle.

[Explanation of symbols]

 1 Water Spraying Device 11 Compressor 12 Drive Shaft 13 Turbine 14 Discharge Port 15 Heat Exchanger 16 Combustor 17 Intake Port 18 Compressed Gas Supply Flow Path 19 Exhaust Port 20 Exhaust Flow Path

Claims (1)

[Claims]
1. A compressor, a turbine, a compressed gas supply flow path from a discharge port of the compressor to a suction port of the turbine via a heat exchanger and a combustor, and an exhaust port of the turbine, In the gas turbine provided with an exhaust flow path for exchanging heat with the compressed gas supply flow path in the heat exchanger via the heat exchanger, between the heat exchanger and the discharge port. A gas turbine characterized in that it is formed by providing water spraying means for spraying water in the compressed gas supply flow path part.
JP18095092A 1992-07-08 1992-07-08 Gas turbine Pending JPH0626361A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP18095092A JPH0626361A (en) 1992-07-08 1992-07-08 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP18095092A JPH0626361A (en) 1992-07-08 1992-07-08 Gas turbine

Publications (1)

Publication Number Publication Date
JPH0626361A true JPH0626361A (en) 1994-02-01

Family

ID=16092114

Family Applications (1)

Application Number Title Priority Date Filing Date
JP18095092A Pending JPH0626361A (en) 1992-07-08 1992-07-08 Gas turbine

Country Status (1)

Country Link
JP (1) JPH0626361A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000043658A1 (en) * 1999-01-25 2000-07-27 Hitachi, Ltd. Gas turbine generating method and generator
US7100359B2 (en) 2001-07-26 2006-09-05 Hitachi, Ltd. Gas turbine installation

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000043658A1 (en) * 1999-01-25 2000-07-27 Hitachi, Ltd. Gas turbine generating method and generator
US7100359B2 (en) 2001-07-26 2006-09-05 Hitachi, Ltd. Gas turbine installation

Similar Documents

Publication Publication Date Title
US9745887B2 (en) Engine cooling system
JP4285781B2 (en) Gas turbine power generation equipment
JP4627907B2 (en) Method and apparatus for supplying cooling air to a turbine engine
CA2507977C (en) Method and apparatus for operating an intercooler for a gas turbine engine
US4179892A (en) Internal combustion engine with exhaust gas recirculation
KR100727709B1 (en) System and method for determining gas turbine firing and combustion reference temperatures having correction for water content in combustion air
US7225762B2 (en) Spraying method and apparatus
US6772596B2 (en) Gas turbine installation
US5513488A (en) Power process utilizing humidified combusted air to gas turbine
EP2357351B1 (en) Exhaust gas recirculation (EGR) system and Power System
US7104071B2 (en) Method for operating a gas turbine group
JP4381572B2 (en) Method for reducing nitrogen oxide (NOX) emissions from positive displacement engines
FI112272B (en) A method for supplying steam to an intake air from an internal combustion engine and a device therefor
US4050239A (en) Thermodynamic prime mover with heat exchanger
CN100429387C (en) Heat and electric power supply system and operation method thereof
CA1331522C (en) Apparatus and method for optimizing the air inlet temperature of gas turbines
US4719746A (en) Gas turbine with a pressure wave machine as the high pressure compressor part
KR960041643A (en) Cooling Apparatus of Turbochargerd Engine
US4010613A (en) Turbocharged engine after cooling system and method
US20090013977A1 (en) Intake condensation removal for internal combustion engine
US6250064B1 (en) Gas turbine inlet air integrated water saturation and supersaturation system and related process
CA2214826C (en) Gas turbine stationary blade
KR20000010648A (en) Steam cooling burner and fuel heating system related with transition
US5160096A (en) Gas turbine cycle
CA2392921A1 (en) Integrated egr valve and cooler