WO2018119577A1

WO2018119577A1 - Novel variable-cycle gas turbine, compressor set thereof and starting method therefor

Info

Publication number: WO2018119577A1
Application number: PCT/CN2016/112109
Authority: WO
Inventors: 胡秀文
Original assignee: 深圳智慧能源技术有限公司
Priority date: 2016-12-26
Filing date: 2016-12-26
Publication date: 2018-07-05

Abstract

A gas turbine, comprising a combustion chamber (12), a turbine (14), and a compressor (16), and further comprising an injection-driven dual-working medium compressor (10). The injection-driven dual-working medium compressor supplies fuel gas-air mixed compressed gas to a combustion chamber by injecting air through jetting of fuel gas, and the supplied fuel gas-air mixed compressed gas is combusted in the combustion chamber in order to start the gas turbine. After a preset working point of the gas turbine is up, the injection-driven dual-working medium compressor stops injecting air. Also disclosed are a compressor set of the gas turbine and a method for starting the gas turbine.

Description

Novel variable cycle gas turbine and its gas compressor unit and starting method

[0001] The present invention relates to a gas turbine, and more particularly to a novel variable cycle gas turbine capable of realizing black start of a gas turbine, a compressor unit thereof, and a starting method.

Background technique

[0002] At present, gas turbine compressors mainly include axial flow compressors, centrifugal compressors, or axial flow combined compressors. Gas turbine units equipped with these types of compressors require auxiliary power starting at start-up. Then, when the gas turbine is used, it is necessary to install a special auxiliary power system, which causes the unit to be complicated.

technical problem

In view of this, the present invention proposes a novel variable cycle gas turbine that can improve the startup mode of an existing gas turbine.

The present invention also provides a gas turbine compressor unit that can realize black start.

The present invention also provides a gas turbine startup method that can achieve black start.

Problem solution

Technical solution

[0006] A novel variable cycle gas turbine includes a combustion chamber, a turbine, and a compressor, the combustion chamber including a combustion chamber inlet and a combustion chamber outlet, the turbine including a turbine inlet and a turbine outlet, the turbine inlet Communicating with the combustion chamber outlet, the compressor is coupled to the turbine drive and includes a compressor inlet and a compressor outlet, the compressor inlet for receiving air, and an ejector duplex refrigerant compressor, The ejector type dual-compressor compressor is configured to use a jet of gas to inject air to provide a gas-air mixed compressed gas to the combustion chamber, and the supplied gas-air mixed compressed gas is combusted in the combustion chamber to start the The gas turbine, when the gas turbine reaches a preset operating point, the ejector duplex compressor stops emitting air.

[0007] In an embodiment, the ejector duplex compressor includes a mixing chamber and at least a first-stage atmospheric absorption chamber and a pressure expansion chamber in communication with the mixing chamber, the atmospheric absorption chamber including a ejector opening for injecting air, a gas nozzle is disposed at the ejector opening, the diffuser chamber includes a mixed gas outlet, and the combustion chamber inlet It is in communication with the mixed gas outlet.

In an embodiment, the compressor outlet is in communication with the mixing chamber.

In an embodiment, the compressor outlet is in communication with the combustion chamber.

[0010] In an embodiment, the atmospheric absorption chamber is closable, and when the gas turbine reaches the preset operating point, the bow-I-bi-type dual-compressor compressor closes the atmospheric absorption chamber. To stop the bow I shoot the air.

[0011] In an embodiment, the preset operating point is a self-sustaining state of the gas turbine.

[0012] A gas turbine compressor unit, the compressor unit includes: an ejector type dual-compressor compressor, wherein the ejector-type dual-mass compressor is used to inject air from a gas to the gas turbine a combustion chamber provides a gas-air mixed compressed gas, the supplied gas-air mixed compressed gas is combusted in the combustion chamber to start the gas turbine; and a second compressor is connected to a turbine drive of the gas turbine, The second compressor is caused to compress air under the drive of the turbine to provide compressed air required for operation of the gas turbine.

[0013] In an embodiment, the second compressor is an axial compressor or a centrifugal compressor, and the compressed gas of the second compressor is introduced into a combustion chamber of the gas turbine, or the second A portion of the compressed gas of the compressor is passed into the bow-ion dual-compressor compressor and another portion is passed to the combustion chamber of the gas turbine.

[0014] In an embodiment, the compressor unit operates as follows: When the gas turbine reaches a self-sustaining state, the compressed air required for operation of the gas turbine is all provided by the second compressor.

[0015] A method for starting a gas turbine, comprising: injecting gas into an ejector duplex compressor to induce air to form a gas-air mixed compressed gas; and introducing the mixed compressed gas into a combustion chamber of the gas turbine Burning; combustion products discharged from the combustion chamber drive turbine rotation of the gas turbine; the turbine drives an axial flow compressor or a centrifugal compressor connected thereto to compress air, the compressed air as the gas turbine Operating the required compressed air; after the gas turbine reaches a preset operating point, the ejector-type dual-working compressor stops ejector air, and only the axial flow compressor or the centrifugal compressor provides the All compressed air required for gas turbine operation.

Advantageous effects of the invention

Beneficial effect

[0016] In summary, the present invention provides a novel variable cycle gas turbine. The gas turbine is provided with a dual compressor unit, the first compressor is an ejector duplex compressor, and the second compressor is an axial or centrifugal air compressor. Machine. The 吋吋吋双双双双压缩机先先先先先双双双双双双双双双双双双双双双双双双双双双双双双双双When the gas turbine reaches the preset operating point, for example, after reaching the self-sustaining speed, the ejector duplex compressor ejector is closed and the gas turbine is operating normally. The invention utilizes the mechanical energy of the gas to ignite the air, realizes the black start of the gas turbine, does not need an external auxiliary power system, reduces the unit equipment, and reduces maintenance and repair. Moreover, the mixing chamber of the ejector duplex compressor can help the gas and air first mix and then enter the combustion chamber for combustion, and the temperature field distribution in the combustion chamber is more uniform, improving the combustion quality and reducing pollutant emissions.

Brief description of the drawing

DRAWINGS

1 is a schematic flow chart showing an operation of an embodiment of a gas turbine according to the present invention.

2 is a schematic flow chart showing the operation of another embodiment of the gas turbine of the present invention.

3 is a schematic structural view of an injection type duplex refrigerant compressor of the gas turbine of FIG. 1.

4 is a schematic view showing the structure of a two-stage atmospheric absorption chamber of an injection type duplex refrigerant compressor of a gas turbine of the present invention.

Embodiments of the invention

[0021] Before the embodiments are described in detail, it is understood that the invention is not limited to The invention may be embodied in other ways. Further, it should be understood that the phraseology and terminology used herein are for the purpose of description The words "including", "comprising", "having", and the like, are used in this context to include the items listed thereafter, their equivalents, and other additional items. In particular, when describing "a certain component", the present invention does not limit the number of the components to one, and may include a plurality.

As shown in FIGS. 1 and 2, the present invention provides a novel variable cycle gas turbine including an ejector duplex compressor 10, a combustion chamber 12, a turbine 14, and a compressor 16. Among them, the ejector type dual working fluid compressor 10 and the compressor 16 together constitute a compressor unit. The combustion chamber 12 is connected to the ejector duplex compressor 10 and the turbine 14, respectively, and the compressor 16 is connected to the ejector duplex compressor 10 and the combustion chamber 12 (Fig. 1), or the compressor 16 Connected to the combustion chamber 12 (Figure 2). Turbine 14 and compressor 16 are connected via a rotating shaft 18.

[0023] The bow I-beam dual working compressor 10 is used to inject air by using a jet of gas to form a gas and air mixture. The gas is compressed to activate the gas turbine. Specifically, as shown in FIG. 3, the ejector duplex compressor 10 includes a mixing chamber 20 and an atmospheric absorption chamber 22 and a diffuser chamber 24 that communicate with the mixing chamber 20. In the illustrated embodiment, the mixing chamber 20 is hollow tubular, and the atmospheric absorption chamber 22 and the diffuser chamber 24 are disposed at both ends of the mixing chamber 20, respectively. In other embodiments, the atmospheric absorption chamber 22 and the diffuser chamber 24 may also be disposed at other relative locations of the mixing chamber 20.

[0024] The atmospheric absorption chamber 22 includes an ejection port 26 for injecting air, and the ejection opening 26 is tapered in the flow direction of the gas. A nozzle 28 is disposed at the ejector port 26, and the nozzle 28 is connected to the gas pipe to receive gas, such as natural gas. The gas is ejected from the nozzle 28 to form a negative pressure to induce air to enter the mixing chamber and the gas at the ejector port 26. mixing. The diffuser chamber 24 is diverging in the flow direction of the air flow for compressing the mixed gas from the mixing chamber 20, and the diffuser chamber 24 includes a mixed gas outlet 30 for discharging the compressed mixed gas.

[0025] It should be understood that the atmospheric absorption chamber 22 is set to one stage in the present embodiment, and in other embodiments, the atmospheric absorption chamber 22 may be set to multiple stages according to the amount of air ejector.

As shown in FIG. 4, the atmospheric absorption chamber 22 is disposed in two stages, for example, the mixing chamber is divided into two sections, including a first section mixing chamber 23 and a second section mixing chamber 25, and the front end of the second section mixing chamber 25 is disposed. a second ejection opening 27, the secondary arch I ejection port 27 is used to illuminate the air, and the end of the first mixing chamber 23 faces the secondary ejection opening 27 at the front end of the second mixing chamber 25 to The mixed gas in one stage of the mixing chamber 23 is injected into the second stage mixing chamber 25. The secondary ejector air increases the amount of air ejector and promotes combustion.

[0027] In the illustrated embodiment, the ejector duplex compressor 10 further includes a gate for controlling the opening and closing of the ejector port 26, and the damper may be disposed in a main control room of the gas turbine. When the ejector port 26 is closed, the ejector port 26 stops igniting the air. It should be noted that the closing of the ejector port 26 does not affect the nozzle 28 injecting gas into the ejector duplex compressor 10.

[0028] It should be understood that when the atmospheric absorption chamber 22 is provided as a multi-stage crucible, such as the two stages in FIG. 4, the ejector duplex compressor 10 has a bow I port 26 and a secondary bow I port 27 . The 吋 setting in the main control room can control the opening and closing of the ejector port 26 and the secondary ejector port 27 simultaneously or independently. When the ejector duplex compressor 10 has a plurality of ports, the gates can control the opening and closing of all the ejector ports simultaneously or independently.

[0029] The combustion chamber 12 includes a combustor inlet 32 and a combustor outlet 34, wherein the combustor inlet 32 is in communication with the mixed gas outlet 30 to cause the compressed mixed gas to enter the combustor 12 for combustion.

[0030] The turbine 14 includes a turbine inlet 36 and a turbine outlet 38, the turbine inlet 36 being in communication with the combustion chamber outlet 34 such that The combustion products (working fluid) of the combustion chamber enter the turbine 14 to drive the turbine turbine to rotate, and the turbine 14 rotates to drive the compressor 16 to compress the air through the shaft 18. The exhaust gas after work is discharged from the turbine outlet 38 or further processed.

[0031] The compressor 16 may be an axial flow or a centrifugal air compressor. In this embodiment, the compressor is an axial flow air compressor 16 . In the embodiment of Figure 1, compressor 16 includes a compressor inlet 40 and a compressor outlet 42 for receiving air, and a compressor outlet 42 for communication to the mixing of the bow-and-eye dual-compressor 10, respectively. Chamber 20 and combustion chamber 12. A portion of the compressed air of the compressor 16 is passed into the mixing chamber 20 of the ejector duplex refrigerant 10 for mixing with the gas to enhance premixing, and a portion of the air is supplied to the combustion chamber 12 for use as cooling air and/or Secondary air. When the gas turbine reaches the preset operating point 吋, the ejector duplex compressor 10 stops the ejector air, and the compressed air required for the turbulent gas turbine operation is all provided by the compressor 16.

[0032] In other embodiments, the compressor outlet 42 may also be in communication only with the combustion chamber 12, as shown in FIG. In this case, after the preset operating point is reached, the ejector duplex compressor 10 provides only gas, which is mixed with the compressed air provided by the compressor 16 in the combustion chamber 12, which is required in the combustion chamber 12. A gas nozzle connected to the ejector duplex refrigerant 10 is disposed. Alternatively, after the preset operating point is reached, the gas is provided by the other gas passages and not by the dual-system dual-compressor compressor 10.

[0033] The starting method of the gas turbine will be described below in conjunction with the specific operational flow of the gas turbine shown in FIG. After the gas turbine engine is started, the ejector type dual working fluid compressor 10 is started first, and the gas turbine control ejector port is closed so that the ejector port 26 is opened. The gas is injected into the ejector duplex compressor 10 via the nozzle 28, and the gas blasting ejector directs the air from the ejector port 26, and the air and the gas enter the mixing chamber for mixing. It is then compressed in the diffuser chamber 24, compressed and then combusted into the combustion chamber. The burned high-temperature working fluid enters the turbine 14 to work on the turbine turbine, and the work is transmitted to the compressor impeller of the compressor 16 through the rotating shaft 18, and the compressed air impeller performs air compression air on the air and passes the compressed air into the ejector duplex. The mixing chamber 20 of the mass compressor 10 and the combustion chamber 12. The compressed air is introduced into the mixing chamber 20 to enhance the premixing, and the combustion chamber 12 can be used as cooling air and/or secondary air to make the combustion more stable and efficient. The output of the combustion chamber 12 is continuously increased, and the rotational speed of the gas turbine of the turbine 14 and the compressor impeller of the compressor 16 is continuously increased until a preset operating point, such as a self-sustaining state, is reached. Continuing to increase the output of the combustion chamber 12 (e.g., by introducing more fuel), the gas turbine controls the ejector opening such that the primary or multi-stage atmospheric absorption chamber 22 of the ejector duplex compressor 10 is slowly closed. The flow of gas into the nozzle 28 can be automatically adjusted based on the power of the turbine. [0034] In summary, the present invention provides a novel variable cycle gas turbine. The gas turbine is provided with a dual compressor unit, the first compressor is an ejector duplex compressor, and the second compressor is an axial or centrifugal air compressor. The 吋吋吋双双双双压缩机先先先先先双双双双双双双双双双双双双双双双双双双双双双双双双双When the gas turbine reaches the preset operating point, for example, after reaching the self-sustaining speed, the ejector duplex compressor ejector is closed and the gas turbine is operating normally. The invention utilizes the mechanical energy of the gas to ignite the air, realizes the black start of the gas turbine, does not need an external auxiliary power system, reduces the unit equipment, and reduces maintenance and repair. Moreover, the mixing chamber of the ejector duplex compressor can help the gas and air first mix and then enter the combustion chamber for combustion, and the temperature field distribution in the combustion chamber is more uniform, improving the combustion quality and reducing pollutant emissions.

[0035] The concepts described herein may be embodied in other forms without departing from the spirit and scope of the invention. The specific embodiments disclosed are to be considered as illustrative and not restrictive. Therefore, the scope of the invention is to be determined by the appended claims rather Any changes which come within the meaning and range of the claims are intended to be within the scope of the claims.

Claims

Claim

A novel variable cycle gas turbine according to claim 1, wherein said ejector type dual working fluid compressor comprises a mixing chamber and at least one primary atmospheric absorption chamber and a pressure expansion chamber in communication with said mixing chamber, The atmospheric absorption chamber includes an ejection port for ejecting air, a gas nozzle is disposed at the ejection opening, the diffusion chamber includes a mixed gas outlet, and the combustion chamber inlet is in communication with the mixed gas outlet.

A novel variable cycle gas turbine according to claim 2, wherein said compressor outlet is connected to said mixing chamber.

A novel variable cycle gas turbine according to any one of claims 1 to 3, wherein said compressor outlet is in communication with said combustion chamber.

A novel variable cycle gas turbine according to claim 2, wherein said atmospheric absorption chamber is closable, and said ejector duplex refrigerant passes when said gas turbine reaches said predetermined operating point The atmospheric absorption chamber is closed to stop the introduction of air.

A novel variable cycle gas turbine according to claim 5, wherein said predetermined operating point is a self-sustaining state of said gas turbine.

A gas turbine compressor unit, characterized in that: the compressor unit comprises: a bow-I-beam type dual-mass compressor, wherein the bow-I-beam type dual-mass compressor is used to inject air by using a gas jet a combustion chamber of the gas turbine provides a gas-air mixed compressed gas, and the supplied gas-air mixed compressed gas is combusted in the combustion chamber to start the gas turbine;

A second compressor, the second compressor being coupled to the turbine drive of the gas turbine such that the second compressor compresses air under the drive of the turbine to provide compressed air required for operation of the gas turbine.

The novel variable cycle gas turbine according to claim 7, wherein the second compressor is an axial compressor or a centrifugal compressor, and the compressed gas of the second compressor is passed into the combustion of the gas turbine. The chamber, or a portion of the compressed gas of the second compressor, passes into the bow-Ibi duplex compressor and another portion opens into the combustion chamber of the gas turbine. A novel variable cycle gas turbine according to claim 7 or 8, wherein said pressurizing The unit operates as follows: When the gas turbine reaches a self-sustaining state, all of the compressed air required for operation of the gas turbine is provided by the second compressor.

[Claim 10] A method for starting a gas turbine, comprising:

Injecting gas into the bow I-beam duplex compressor to induce air to form a gas-air mixed compressed gas;

Passing the mixed compressed gas into a combustion chamber of the gas turbine for combustion;

The combustion products discharged from the combustion chamber drive turbine rotation of the gas turbine; the turbine drives a second compressor connected thereto to compress air, and the compressed air is used as compressed air required for operation of the gas turbine;

After the gas turbine reaches a preset operating point, the bow-I-bi-type dual-compressor compressor stops the air, and only the axial-flow compressor or the centrifugal compressor provides the gas turbine to operate. All compressed air.