CN104088702B - A kind of compact miniature gas turbine - Google Patents

Abstract

A compact micro gas turbine, mainly including an air inlet, a compressor, a combustion chamber, a turbine, a shaft installation body, a shaft and a casing; the compressor is a single-stage centrifugal compressor, the combustion chamber is a full-ring combustion chamber, and the turbine is a single-stage Centripetal turbine; the inlet port is connected with the front flange by screws; the inner ring of the diffuser and the outer ring of the diffuser are all welded on the front flange; The front end of the mounting body is fixed in the inner ring of the diffuser; the turbine and the shaft are processed as one, and after the turbine shaft passes through the shafting mounting body, the compressor is installed on the front end of the turbine shaft and locked with the compressor wheel lock nut; the shafting mounting body The rear end is screwed to the front end of the turbine mounting plate, and the rear end of the turbine mounting plate is fixed to the front end of the turbine guide; the combustion chamber is placed outside the shaft installation body, and axially covers the front half of the turbine. Turning to the radial direction, passing through the turbine guide, and impacting the turbine; the turbine guide, the rear end of the combustion chamber, and the turbine casing are collectively fixed with the rear flange.

Description

A compact micro gas turbine

technical field

The invention relates to a gas turbine, in particular to a compact micro gas turbine.

Background technique

Micro gas turbine refers to a low-power gas turbine with a stand-alone power within hundreds of kilowatts. It can use natural gas, biogas, gasoline, diesel and alkanes as fuel. Micro gas turbines can be used as the core device of distributed energy technology to realize efficient energy utilization of combined cooling, heating and power. Micro gas turbines can also be used in aviation, aerospace and other fields, and can also be used in military vehicle auxiliary power units, vehicle hybrid power units, etc.

Micro gas turbines developed earlier in foreign countries. The United States, Japan and some European countries are researching micro gas turbines and developing their application functions. Now a variety of products have entered the market. Domestically, micro gas turbines are a major project in the field of energy technology in the "10th Five-Year Plan" national "863" plan. After the first stage of research, we have initially mastered the design and manufacture of complete sets of micro gas turbines. But so far, there is no completely self-developed micro gas turbine used in commercial operation in China. Most of the micro gas turbine generating sets produced in China use foreign micro gas turbines, and they only design accessories such as generators and regenerators. Some micro gas turbines use a single-tube combustor, the distance from the compressor outlet to the combustor inlet is long and there are several deflections, the airflow pressure loss is large, and the volume is also large. In order to be commercialized and widely used, the micro gas turbine needs to reduce its manufacturing cost, make it small in size, high in efficiency and easy in maintenance.

Contents of the invention

The technical problem to be solved by the present invention is: make full use of the existing domestic technology, develop a compact micro gas turbine with low cost, easy to manufacture, compact structure and good performance, and carry out the overall design of the micro gas turbine so that it can be used as a distributed energy source And core devices such as auxiliary power units.

The technical solution adopted by the present invention to solve its technical problems: a compact micro gas turbine, characterized in that it includes an air inlet, a compressor, a combustion chamber, a turbine, a shaft installation body, a shaft and a casing; the compressor is a single-stage centrifugal Compressor, the combustion chamber is a full-ring combustion chamber, and the turbine is a single-stage centripetal turbine; the inlet port is connected with the front flange by screws; the inner ring of the diffuser and the outer ring of the diffuser are all welded on the front flange, and the airflow passes through The rear direction of the diffuser is changed from radial to axial, and the front end of the shaft installation body is fixed in the inner ring of the diffuser; the turbine and the shaft are processed as one, and after the turbine shaft passes through the shaft installation body, the compressor is installed on the turbine shaft The front end is locked with the lock nut of the compressor wheel; the rear end of the shaft installation body is connected with the front end of the turbine installation plate by screws, and the rear end of the turbine installation plate is fixed to the front end of the turbine guide; the combustion chamber is placed outside the shaft installation body, parallel to the shaft To cover the front half of the turbine, the direction of the airflow after passing through the combustion chamber changes from axial to radial, and passes through the turbine guide to impact the turbine; the turbine guide, the rear end of the combustion chamber, and the turbine casing are collectively fixed with the rear flange.

The air flow rate of the micro gas turbine is 0.1-2kg/s, the rotational speed of the shaft system is 5000-6000r/min when it is ignited, and the rated rotational speed is 50000r/min.

The boost ratio of the compressor is 2.5-3, and the turbo expansion ratio is 1.3-2.45.

The diffuser is composed of three parts: a vaneless radial diffuser section, a turning section and an axial diffuser section, and is surrounded by a front flange, a shaft installation body, an inner diffuser ring and an outer diffuser ring.

The number of blades of the turbine guider is 20.

The working principle of the present invention is as follows: after the air passes through the air inlet, it enters the centrifugal compressor, is compressed and pressurized therein, and then enters the diffuser, and the direction changes from radial direction to axial direction, and then enters the combustion chamber. At the same time, the motor drives the fuel pump, and the fuel is sprayed into the combustion chamber through the nozzle and mixed with compressed air for combustion to generate high-temperature gas. The cooling air coming in from the mixing hole at the rear end of the combustion chamber will be mixed with the high-temperature gas to make the mixture reach the temperature that the turbine can withstand. At the end of the combustion chamber, the direction of the airflow changes from axial to radial. Through the turbine guide, it expands, and part of the heat energy is converted into kinetic energy, forming a high-speed airflow. Then hit the centripetal turbo. The rotation of the turbine produces mechanical work. Lubrication is required during the rotation of the shaft system. The motor drives the lubricating oil pump, passes through the lubricating oil pipeline and oil filter, and then enters the shafting installation body to play the role of lubrication and cooling, and then returns to the lubricating oil tank through the oil return pipeline.

Compared with the prior art, the present invention has the following advantages:

(1) The micro gas turbine of the present invention is easy to process, small in size, low in cost, and can move freely;

(2) The micro gas turbine of the present invention adopts a full annular combustion chamber, and is placed outside the shaft installation body, and axially covers the first half of the turbine, shortening the axial distance and making full use of the space;

(3) In the micro-gas turbine of the present invention, after the air-flow comes out from the centrifugal compressor, it turns ninety degrees and enters the combustion chamber, and the pressure loss of the air-flow is smaller than using the two ninety-degree turns of the single-pipe combustion chamber;

(4) micro gas turbine of the present invention adopts single-stage centripetal turbine, and efficient is high, and impeller has better intensity and rigidity, has used turbine guider again, and whole centripetal turbine structure is very simple, is easy to manufacture.

Description of drawings

Fig. 1 is a micro-gas turbine structural representation of the present invention;

Fig. 2 is the structural representation of diffuser of the present invention;

Fig. 3 is a schematic structural view of the turbine guide of the present invention;

In the figure: 1 intake port, 2 compressor, 3 combustion chamber, 4 turbine, 5 shaft mounting body, 6 shaft, 7 fuel inlet, 8 fuel pipe, 9 nozzle, 10 lubricating oil inlet, 11 lubricating oil inlet pipe, 12 Lubricating oil outlet pipe, 13 Lubricating oil outlet, 14 Diffuser, 15 Front flange, 16 Turbine installation plate, 17 Turbine guider, 18 Turbine installation positioning ring, 19 Shell, 20 Diffuser inner ring, 21 Diffuser Device outer ring, 22 compressor wheel lock nut, 23 igniter, 24 turbine casing, 25 rear flange, 26 turbine guide front mounting plate, 27 turbine guide vane, 28 turbine guide rear mounting plate.

detailed description

The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

A micro gas turbine of this embodiment comprises a compressor 2, a combustion chamber 3, a turbine 4, a shaft installation body 5, a shaft 6, and a casing 19; the compressor 2 is a single-stage centrifugal compressor; the combustion chamber 3 is a full annular combustion chamber; the turbine 4 is a single-stage centripetal turbine; as shown in Figure 1, the intake duct 1 is connected with the front flange 15 by screws, and is mounted on the front end of the compressor 2, and the air enters the compressor through the intake duct 1; the diffuser Both the inner ring 20 and the diffuser outer ring 21 are welded on the front flange 15 (as shown in Fig. 2 ), the diffuser inner ring 20 has bolt holes, and the diffuser inner ring 20 and the front end of the shaft installation body 5 The outer diameter is clearance fit, and the shaft installation body 5 is fixed to the diffuser inner ring 20 with pressing pieces and screws, so that the front flange 15, the diffuser outer ring 21, the diffuser inner ring 20 and the shaft installation body 5 surrounds the diffuser 14, which is divided into three parts: the radial diffuser section, the turning section and the axial section, which convert the air compressed by the compressor 2 from radial to axial; the turbine 4 and the shaft 6 process As a whole, after passing through the turbine installation positioning ring 18, insert it from the rear end of the shafting installation body 5, and the front end of the shaft 6 protrudes from the shafting installation body 5, install the compressor 2 on the front end of the shaft 6, and then use the compressor wheel The lock nut 22 locks the compressor 2, that is, the compressor 2 is connected to the turbine 4 in a single shaft; after the turbine mounting plate 16 is positioned by the turbine mounting positioning ring 18, it is connected with the rear end of the shafting mounting body 5 with screws, and the turbine mounting plate 16 The rear end is also screwed to the turbine guide 17, and the turbine guide 17 is welded on the turbine guide mounting plate 26 and the turbine guide rear mounting plate (as shown in Figure 3) by 20 turbine guide blades 27, and the airflow passes through the turbine guide After the guide 17, the thermal energy is converted into kinetic energy, and the speed increases; the fuel pipe 8 is divided into two sections, fixed on the periphery of the diffuser outer ring 21 with bolts, and connected with the fuel inlet 7, and the end of the fuel pipe 8 is threaded, installed Nozzle 9, the nozzle 9 is a centrifugal nozzle, the nozzle 9 is inserted into the front end of the combustion chamber 3; the motor drives the fuel pump, and the fuel is sprayed into the combustion chamber through the fuel inlet 7, the fuel pipe 8, and the nozzle 9; the combustion chamber 3 can be divided into straight sections , the oblique section and the vertical section, which are placed outside the shaft installation body 5, axially cover the first half of the turbine 4, and the air flow passes through the combustion chamber 3, turning from the axial direction to the radial direction; the rear end of the combustion chamber 3 has a threaded hole, The corresponding position of the fixed turbine guide 17 rear end is also provided with threaded holes, the turbine housing 24 is correspondingly externally drilled through holes, and the corresponding position of the rear flange 25 is drilled through holes, screwed in from the rear flange 25 with screws, and the turbine guide 17 is screwed in. , the combustion chamber 3, the turbine casing 24 and the rear flange 25 are fixed; when the shafting speed reaches a certain speed, the igniter 23 realizes the ignition of the combustion chamber; Lubricating oil is introduced into the shaft system, and the lubricating oil plays the role of lubricating the shaft and cooling the heat of the shaft and the turbine end, and then relies on gravity to flow back to the oil tank from the lubricating oil outlet pipe 12 through the lubricating oil outlet 13; there are flanges at the front and rear of the casing 19 , respectively connected with the front flange 15 and the rear flange 25 by bolts.

Claims (3)

1. A compact micro gas turbine, characterized in that: comprise air intake (1), compressor (2), combustion chamber (3), turbine (4), shafting mounting body (5), shaft (6) and The casing (19); the compressor (2) is a single-stage centrifugal compressor, the combustion chamber (3) is a full-ring combustion chamber, and the turbine (4) is a single-stage centripetal turbine; the air inlet (1) and the front flange ( 15) Screw connection; the diffuser inner ring (20) and the diffuser outer ring (21) are all welded on the front flange (15), and the direction of the airflow after passing through the diffuser (14) changes from radial to axial , the front end of the shafting mounting body (5) is fixed in the diffuser inner ring (20); the turbine (4) and the shaft (6) are processed as one, and after the turbine shaft passes through the shafting mounting body (5), the compressor ( 2) Install on the front end of the turbine shaft and lock it with the compressor wheel lock nut (22); the rear end of the shaft installation body (5) is connected with the front end of the turbine mounting plate (16) by screws, The front end of the guide (17) is fixed; the combustion chamber (3) is placed outside the shaft installation body (5), and axially covers the front half of the turbine (4), and the direction of the airflow after passing through the combustion chamber (3) changes from axial to Radially, through the turbine guide (17), impact the turbine (4); the turbine guide (17), the rear end of the combustion chamber (3), the turbine casing (24) are collectively fixed with the rear flange (25); The air flow rate is 0.1-2kg/s, the shafting speed is 5000-6000r/min during ignition, and the rated speed is 50000r/min; The boosting ratio of the compressor (2) is 2.5-3, and the expansion ratio of the turbine (4) is 1.3-2.45. 2. A kind of compact micro gas turbine according to claim 1, characterized in that: the diffuser (14) is composed of three parts, a vaneless radial diffuser section, a turning section and an axial diffuser section, and consists of a front flange (15), shaft installation body (5) front end, diffuser inner ring (20) and diffuser outer ring (21) enclose. 3. A kind of compact micro gas turbine according to claim 1, characterized in that: the number of blades of the turbine guide (17) is 20.