CN108952964A - A kind of gas-turbine unit of single composite impeller - Google Patents

Abstract

The invention discloses a gas turbine engine with a single composite impeller, which mainly includes: a composite impeller in which a centrifugal compressor blade and a hollow turbine blade are combined into one, a main shaft, a starter motor, a clutch, a bearing, a rectifying support, and an annular swirl combustion chamber , ring casing assembly, tail cone, tail nozzle, the main shaft is fixedly connected with the composite impeller, the starter is connected to the main shaft through a clutch, the main shaft is installed in the shaft sleeve through two bearings, and the rectifying bracket is connected with the ring casing assembly. Mounting clips are arranged on the annular casing assembly to be fixed on the aircraft. The annular swirl combustion chamber is located in the annular casing assembly, the tail cone is located at the rear of the impeller, and the tail nozzle is connected with the casing assembly as a whole. The invention has the advantages of simplified engine structure, reduced weight, improved mechanical rotation performance of the rotor, reduced cost, effective use of compressed air flow to cool down the hollow turbine blades, and further improved engine performance and service life.

Description

A gas turbine engine with a single compound impeller

technical field

The invention relates to the field of gas turbines, in particular to a gas turbine engine with a single compound impeller.

Background technique

In the field of aviation, with the development of aviation technology, unmanned aerial vehicles and light aircraft have gradually become one of the most attractive products. However, the lightness and high efficiency of the power plant is the key technology that restricts the development of the above-mentioned aircraft. The demand and development of micro-turbine engines is getting faster and faster, which is an important branch of aeroengines. It mainly provides the required power for unmanned aerial vehicles, cruise missiles, light aircraft, etc., and can also provide electricity and power for ground devices. The usual micro-turbine engine is mainly composed of a transmission shaft connecting the centrifugal compressor and the radial turbine or axial flow turbine to form a rotor rotating part. The small rotor has a high speed and a large span, and it is difficult to control the rotation accuracy and vibration stability of the rotor. Simultaneously, due to structural cost constraints, the usual tiny engine does not cool the turbine, which greatly reduces the life of the turbine and the performance of the engine, seriously affecting its development and application. Aiming at the above problems, the present invention proposes a new compound impeller structure of micro-turbine engine, which combines the compressor and the turbine into one, which greatly simplifies the rotor structure, reduces the weight and cost, and improves the mechanical rotation performance of the rotor. At the same time, it can effectively use the compressed airflow to cool the turbine impeller, thus creating conditions for increasing the temperature before the turbine or reducing the material requirements of the turbine, which is conducive to further improving engine performance and life.

Contents of the invention

In order to solve the above technical problems, the present invention provides a gas turbine engine with a single composite impeller.

The present invention adopts the following technical scheme: a gas turbine engine with a single composite impeller, including a starter motor, a clutch, a main shaft, a bearing, a rectifying bracket, a composite impeller in which the blades of the centrifugal compressor and the hollow turbine blades are smoothly connected as one, and an annular swirl type The combustor, the annular casing assembly, the tail cone, the tail nozzle, the radial channel on the outer edge of the centrifugal compressor blade and the hollow turbine blade are smoothly connected together to form a compound impeller with dual functions of compressing gas and expanding to do work. The starter motor passes through the clutch It is connected to one end of the main shaft, and the other end of the main shaft is fixedly connected to the centrifugal compressor blade in the composite impeller. The outer surface on the right side of the starter motor is evenly connected to one end of three connecting rods, and the other end of the connecting rod is fixedly connected to the rectifying bracket. Clutch, main shaft 1. The bearing is located in the shaft sleeve, and the two ends of the main shaft are sleeved with bearings. The outer surface of the shaft sleeve is evenly equipped with three rectifying brackets. The flow combustor is located in the annular casing assembly, and the inner ring of the annular casing assembly is connected with the inner ring of the annular swirl type combustor, and the annular swirl type combustor adjusts the peripheral velocity of the outlet airflow of the centrifugal compressor blade in the annular swirl type The combustion chamber continues to maintain and burns and heats up and accelerates to directly drive the hollow turbine blades. The rotation of the hollow turbine blades drives the rotation of the centrifugal compressor blades. The right side of the annular casing assembly is fixedly connected with the tail nozzle, and the tail cone is located behind the centrifugal compressor blades. part, and connected with the tail nozzle as a whole, the annular casing assembly is provided with a hoop, which is used to fix the gas turbine engine with a single compound impeller to the aircraft.

Working principle: In the present invention, the outer edge radial channels of the centrifugal compressor blades are smoothly connected with the hollow turbine blades to form a compound impeller with dual functions of compressing gas and expanding work. The peripheral speed continues to be maintained in the annular swirling combustion chamber and drives the hollow turbine blades. The main shaft is fixedly connected to the composite impeller. The starter motor is connected to the main shaft through the clutch. The main shaft is installed in the shaft sleeve through the bearing. , the annular swirling combustor is located in the annular casing assembly, the tail cone is located at the rear of the composite impeller, the tail nozzle is connected with the annular casing assembly as a whole, and a hoop is installed on the annular casing assembly for A gas turbine engine with a single compound impeller affixed to the aircraft.

The invention has the advantages: the rotor of a gas turbine engine with a single compound impeller can effectively simplify the structure, reduce the weight, reduce the cost, improve the mechanical rotation performance of the rotor, and at the same time effectively use the compressed air flow to cool the turbine impeller, thereby It creates conditions for increasing the temperature before the turbine or reducing the material requirements of the turbine, which is conducive to further improving engine performance and life.

Description of drawings

Fig. 1 is a schematic structural view of a gas turbine engine with a single compound impeller according to the present invention.

Fig. 2 is a schematic diagram of the structural principle of a gas turbine engine with a single compound impeller according to the present invention.

Fig. 3 is a structural schematic diagram of a compound impeller in a gas turbine engine with a single compound impeller according to the present invention. Explanation of reference numerals: 1, starter motor 2, clutch 3, main shaft 4, bearing 5, rectifying bracket 6, centrifugal compressor blade 7, hollow turbine blade 8, annular swirling combustion chamber 9, annular casing assembly 10, tail Cone 11, tail nozzle I, low temperature air II, high temperature air III, high temperature gas IV, low temperature gas A, hollow turbine outer passage B, hollow turbine blade inner passage C, centrifugal compressor impeller.

Detailed ways

The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, so as to define the protection scope of the present invention more clearly.

Please refer to Figures 1, 2, and 3, a gas turbine engine with a single compound impeller, including a starter motor (1), a clutch (2), a main shaft (3), a bearing (4), a rectifying bracket (5), a centrifugal Compressor blade (6), hollow turbine blade (7), annular swirl combustor (8), annular casing assembly (9), tail cone (10), tail nozzle (11), centrifugal compressor blade The outer radial channel of (6) is smoothly connected with the hollow turbine blade (7) to form a composite impeller with dual functions of compressing air and expanding work. The starter motor (1) is connected to one end of the main shaft (3) through the clutch (2). The other end of the main shaft (3) is fixedly connected with the centrifugal compressor blade (6) in the composite impeller, and the outer surface on the right side of the starter motor (1) is evenly connected with one end of three connecting rods, and the other end of the connecting rod is connected with the rectifying bracket ( 5) Fixed connection, the clutch (2), the main shaft (3), and the bearing (4) are set in the shaft sleeve, and the two ends of the main shaft (3) are sleeved with bearings (4), and the outer surface of the shaft sleeve is evenly equipped with three rectifying brackets (5 ), the outer surface of the shaft sleeve is welded to one end of the rectifying bracket (5), and the other end of the rectifying bracket (5) is fixedly connected to the annular casing assembly (9), and the annular swirling combustion chamber (8) is located in the annular casing assembly (9 ), the inner ring of the annular casing assembly (9) is connected with the inner ring of the annular swirl combustor (8), and the annular swirl combustor (8) reduces the peripheral velocity of the outlet airflow of the centrifugal compressor blade (6) Continue to maintain in the annular swirling combustion chamber (8) and directly drive the hollow turbine blades (7) after combustion and heating acceleration, the hollow turbine blades (7) rotate to drive the centrifugal compressor blades (6) to rotate, and the annular casing assembly (9 ) right side is fixedly connected with the tail nozzle (11), the tail cone (10) is located at the rear of the centrifugal compressor blade (6), and is connected with the tail nozzle (11) as a whole, the annular casing assembly (9) is provided with a hoop for fixing the gas turbine engine with a single composite impeller to the aircraft.

The centrifugal compressor blade (6) and the hollow turbine blade (7) are integrated by 3D printing processing technology, and the low-temperature air (I) compressed by the centrifugal compressor impeller (D) continues to be centrifuged through the inner channel (B) of the hollow turbine blade. Compression and expansion can effectively cool the hollow turbine blades (7); the starter motor (1) is connected to the main shaft (3) through the clutch (2), and the two bearings (4) are used to support the main shaft (3) and connect with the main shaft (3). The rectifying support (5) is fixedly connected, the rectifying support (5) is connected with the annular casing assembly (9), and the annular swirl combustion chamber (8) is located in the casing assembly 9, and the compressed high-temperature air passing through the turbine hollow passage (B) (II) Swirling combustion in the annular swirling combustion chamber (8), after combustion, the high-speed, high-temperature gas (Ⅲ) expands through the outer channel (A) of the hollow turbine to do work, driving the compound impeller to rotate, and the tail cone (10) is fixed on The afterbody of the composite impeller, the tail nozzle (11) is connected with the annular casing assembly (9), so that the low-temperature gas (IV) passing through the hollow turbine blade (7) is ejected at a high speed through the tail nozzle (10).

It is not limited thereto, and any changes or replacements that do not go through creative efforts shall fall within the scope of protection of the present invention. Therefore, the protection scope of the present invention should be determined by the protection scope defined in the claims.

Claims (3)

1. a kind of gas-turbine unit of single composite impeller, which is characterized in that the outer rim of centrifugal compressor blade (6) is radial Channel and hollow turbine vane (7), which are smoothly connected, collectively constitutes one with the compound leaf calmed the anger with expansion work dual function The peripheral speed of centrifugal compressor exit flow is continued to keep simultaneously combustion heating in combustion chamber by wheel, annular swirl combustion chamber (8) Hollow turbine vane (7) are directly driven after acceleration.

2. a kind of gas-turbine unit of single composite impeller according to claim 1, which is characterized in that single compound The gas-turbine unit of impeller include starting motor (1), clutch (2), main shaft (3), bearing (4), rectification bracket (5), from Heart compressor blade (6) and hollow turbine vane (7) be smoothly connected the composite impeller being integrated, annular turbulence-type combustion chamber (8), Annular case component (9), tail cone (10), jet pipe (11), starting motor (1) pass through clutch (2) and main shaft (3) one end phase Even, main shaft (3) other end is fixedly connected with the centrifugal compressor blade (6) in composite impeller, and main shaft (3) two sides are arranged bearing (4), annular turbulence-type combustion chamber (8) is located in annular case component (9), annular case component (9) right side and jet pipe (11) be fixedly connected, tail cone (10) is located at centrifugal compressor blade (6) rear portion, and with jet pipe (11) be connected to one it is whole Body.

3. a kind of gas-turbine unit of single composite impeller according to claim 1, which is characterized in that the clutch Device (2), main shaft (3), bearing (4) are distributed in axle sleeve, and sleeve outer surface is uniformly provided with three rectification brackets (5), axle sleeve appearance Face and rectification bracket (5) one end are welded, and rectification bracket (5) other end is fixedly connected with annular case component (9).