CN114483304B

CN114483304B - Novel variable circulation turboshaft engine structure

Info

Publication number: CN114483304B
Application number: CN202210110673.7A
Authority: CN
Inventors: 聂建豪; 陶建军; 曾飞; 王芳
Original assignee: Hunan Aviation Powerplant Research Institute AECC
Current assignee: Hunan Aviation Powerplant Research Institute AECC
Priority date: 2022-01-29
Filing date: 2022-01-29
Publication date: 2023-09-26
Anticipated expiration: 2042-01-29
Also published as: CN114483304A

Abstract

The application discloses a novel variable-circulation turboshaft engine structure, which comprises an engine outer casing, wherein a core engine, an outer duct, a power rotor and a geometric adjustable mechanism are arranged in the engine outer casing; the air flow enters the outer casing from the air inlet, the fan rotor and the fan guide vane divide the air flow into an inner air flow and an outer air flow, the first air flow continuously passes through the core machine, the second air flow passes through the outer duct, the geometric adjustable mechanism is used for mixing the second air flow with the first air flow, the geometric adjustable mechanism can adjust the flow area of the mixed air flow, the mixed air flow flows to the power turbine guide vane, so that the power turbine rotor is driven to do work, and finally the air flow is discharged from the exhaust frame; a transmission device for outputting power is connected to the power turbine rotor.

Description

Novel variable circulation turboshaft engine structure

Technical Field

The application belongs to the technical field of turboshaft engines, and particularly relates to a novel variable-circulation turboshaft engine structure.

Background

At present, the research direction of the variable cycle gas turbine engine at home and abroad mainly focuses on the variable cycle turbofan engine, as shown in figure 1, and is a development profile of 5 generations of VCE. The key component of the first generation is VABI, which has typical characteristics of adjustable bypass ratio; the key component of the second generation is CDFS, which has the typical feature of complex multivariable regulation; the key components of the third generation are CDFS and FADEC, which are typically characterized by adaptive mode selection valves; the key components of the fourth generation are an area-adjustable high-pressure turbine guide, a single-stage high-load transonic high-pressure turbine and a double-stage guide vane-free contra-rotating low-pressure turbine, and the typical characteristic of the fourth-generation high-pressure turbine guide is a controllable pressure ratio; the key components of the fifth generation are CDFS and flight, which have the typical feature of adaptive loops. However, in the foregoing, there is little concern about variable cycle turboshaft engines. The cross-sectional shape of the turboshaft engine in service at present is shown in figure 2. As can be seen from the drawings, the turboshaft engine currently in service generally comprises a rear variable area ejector, a first outer duct, a CDFS, a second outer duct, a mode selection valve, a fly, and a third outer duct. The structure is cyclic and not adjustable.

According to the above related art, the inventors consider that the scroll engine is cyclical and not adjustable. Resulting in difficulty in achieving both low and high speed flight performance advantages.

Disclosure of Invention

Aiming at the problems, the application provides a novel variable-circulation turboshaft engine structure which has stronger circulation adjusting capability and task adaptability compared with the existing turboshaft engine.

The novel variable-circulation turboshaft engine structure comprises an engine outer casing, wherein a core engine, an outer duct, a power rotor and a geometrically adjustable mechanism are arranged in the engine outer casing, an air inlet and an exhaust frame are arranged on the engine outer casing, the core engine comprises a fan rotor, a fan guide vane is further arranged in the engine outer casing, and the power rotor comprises a power turbine rotor and a power turbine guide vane; the air flow enters the outer casing from the air inlet, the fan rotor and the fan guide vane divide the air flow into an inner air flow and an outer air flow, the first air flow continuously passes through the core machine, the second air flow passes through the outer duct, the geometric adjustable mechanism is used for mixing the second air flow with the first air flow, the geometric adjustable mechanism can adjust the flow area of the mixed air flow, the mixed air flow flows to the power turbine guide vane, so that the power turbine rotor is pushed to do work, and the exhaust frame is used for exhausting the air flow; the power turbine rotor is connected with a transmission device which is used for outputting power.

Further, the core machine comprises two stages of rotors, namely a high-pressure rotor and a low-pressure rotor, wherein the high-pressure rotor comprises a high-pressure compressor rotor, a high-pressure turbine rotor and a connecting shaft between the high-pressure compressor rotor and the high-pressure turbine rotor; the fan rotor belongs to the low-pressure rotor, and the low-pressure rotor further comprises a low-pressure turbine rotor and a connecting shaft for connecting the fan rotor and the low-pressure turbine rotor.

Further, the core machine comprises three or more stages of rotors.

Further, the core machine comprises a combustion chamber, and the structure of the combustion chamber comprises a direct-current type, a backflow type or a three-stage type.

Further, a compressor stator is connected in the outer casing of the engine through a support plate structure, and the compressor stator is positioned between the fan rotor and the combustion chamber.

Further, the compressor guide vane and the power turbine guide vane of the compressor stator are used for adjusting the flow area of the air flow.

Further, the power rotor is a single-stage rotor or a double-stage rotor or three-stage or more rotors.

Further, the high-voltage rotor is a single-stage rotor or a double-stage rotor or three-stage or more rotors.

Further, the low-voltage rotor is a single-stage rotor or a double-stage rotor or three-stage or more rotors.

Further, the transmission device is a spline or a membrane disc.

Further, the fan rotor is a single-stage rotor or a double-stage rotor.

Through the technical scheme, the vortex shaft engine can be circularly adjustable. When the low-speed flying performance and the high-speed flying performance are simultaneously considered, the variable circulation turboshaft engine has good advantages. Compared with the existing turboshaft engine, the application has stronger circulation adjusting capability and task adaptability.

Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 shows an overview of the development of a 5 generation VCE in the background art.

Fig. 2 shows the structure of a turboshaft engine in the background art.

Fig. 3 shows a schematic cross-sectional view of an engine outer case in the present application.

Reference numerals: 01. a high-pressure rotor; 011. a high pressure compressor rotor; 012. a high pressure turbine rotor; 02. a low pressure rotor; 021. a fan rotor; 022. a low pressure turbine rotor; 03. a power rotor; 032. a power turbine rotor; 033. a spline; 04. a combustion chamber; 111. a compressor stator; 112. a high pressure turbine stator; 121. a fan vane; 122. a low pressure turbine stator; 132. a power turbine vane; 151. an air intake assembly; 152. a support plate; 153. a geometrically adjustable mechanism; 154. an exhaust frame; 155. an air inlet.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

Referring to fig. 3, a novel variable cycle scroll engine structure includes an engine outer casing on which an air inlet 155 and an air outlet are provided. An intake assembly 151 is mounted at the intake 155 and an exhaust frame 154 is mounted at the outlet of the engine outer case. The novel variable-circulation turboshaft engine structure is a three-rotor structure, and the variable-circulation turboshaft engine structure is a high-pressure rotor 01, a low-pressure rotor 02 and a power rotor 03 respectively. The high-pressure rotor 01 includes a high-pressure compressor rotor 011 and a high-pressure turbine rotor 012 and a connecting shaft therebetween; the low pressure rotor 02 includes a fan rotor 021 and a low pressure turbine rotor 022 and a connecting shaft therebetween; the power rotor 03 includes a power turbine rotor 032 and a power turbine output shaft.

Referring to fig. 3, a core engine is provided in an engine outer case, and a high-pressure rotor 01 and a low-pressure rotor 02 are two-stage rotors of the core engine, and a power rotor 03 is also provided in the engine outer case. An outer duct, a geometrically adjustable mechanism 153 and power turbine guide vanes 132 are also provided within the engine outer casing.

Referring to fig. 3, a fan rotor 021 is positioned adjacent to the air intake assembly 151, and a fan vane 121 is installed at the rear end of the fan rotor 021. The compressor stator 111 is installed at the rear end of the fan guide vane 121 in a support plate 152 structure, and the compressor stator 111 is connected with an engine outer casing. The combustion chamber 04 is connected to the rear side of the compressor stator 111, and the combustion chamber 04 has three structures, and any one of a direct-current type, a backflow type or a three-stage type can be selected. A high-pressure turbine stator 112 is mounted at the rear end of the combustion chamber 04, a high-pressure turbine rotor 012 is mounted at the rear end of the high-pressure turbine stator 112, a low-pressure turbine stator 122 is disposed at the rear end of the high-pressure turbine rotor 012, and a low-pressure turbine rotor 022 is located at the rear end of the low-pressure turbine stator 122. A support plate 152 is mounted at the aft end of the low pressure turbine rotor 022, the power turbine vane 132 is mounted at the aft end of the support plate 152, and the support plate 152 and the power turbine vane 132 connect the inner and outer flow passages at the aft end of the centrifuge turbine. A geometrically adjustable mechanism 153 is mounted between the cardboard and the power turbine vanes 132 and can control the airflow flow area. The power turbine rotor 032 is located aft of the power turbine vanes 132 and the exhaust frame 154 is located aft of the power turbine rotor 032. A transmission device for outputting power is connected to the power turbine rotor 032. The transmission is a spline 033 or a membrane disc.

After the air flow enters the outer casing from the air inlet 155, the fan rotor 021 and the fan guide vane 121 divide the air flow into two air flows, namely, the inner air flow and the outer air flow, the first air flow continues to pass through the core machine, and the second air flow flows into the outer duct. After passing through the outer duct, the second air stream is combined with the first air stream and blended under the direction of the geometrically adjustable mechanism 153. By operating the position of the geometrically adjustable mechanism 153, it is thereby possible to have the geometrically adjustable mechanism 153 adjust the flow area of the blended air stream, i.e. the cross-sectional area of the flow channel. After passing through the geometry-adjustable mechanism 153, the blended air flow flows to the power turbine guide vane 132, so that the power turbine rotor 032 is pushed to do work, the internal energy of the air flow is converted into mechanical energy, and the transmission device is driven to output power. Finally the air flow is exhausted from the exhaust frame 154. When the geometrically adjustable mechanism 153 is manipulated to increase the cross-sectional area of the flow passage, the flow rate of the air stream through the geometrically adjustable mechanism 153 is slowed. When the geometry-adjustable mechanism 153 is actuated to reduce the cross-sectional area of the flow channel, the flow rate of the air flow through the geometry-adjustable mechanism 153 is increased. By such a configuration, the pushing power turbine rotor 032 can be changed.

The core machine may also use a greater number of stages of rotors, such as three or four stages of rotors. The power rotor 03 can use rotors with more stages according to practical situations, such as a double-stage rotor or a tripolar rotor. Also, the high pressure turbine may use more stages of rotors, such as a dual stage rotor or a three stage rotor, depending on the actual situation. The low-pressure turbine can also use rotors with more stages, such as a double-stage rotor or a tripolar rotor, according to practical situations. The fan rotor 021 may also use a rotor with more stages, such as a two-stage rotor or a three-stage rotor, according to the actual situation.

In addition to using the geometry-adjustable mechanism 153 to adjust the blended airflow area, the blended airflow area may also be adjusted using the compressor vane adjacent to the compressor stator 111, or using the power turbine vane 132 structure on the aft side of the geometry-adjustable mechanism 153.

Through such setting, the utility model discloses become circulation turboshaft engine structure is through controlling geometric adjustable mechanism 153 to adjust the air current flow area after mixing, when the air current flow area after mixing reduces, because the runner cross section reduces and the flow is unchangeable, can increase the flow velocity of air current, after the flow velocity of air current is fast, when promoting power turbine rotor 032 acting, the pivoted speed of power turbine rotor 032 also is faster, and the mechanical energy that exports to the external world is also higher. When the flow area of the mixed air flow increases, the flow rate is unchanged due to the increase of the cross section of the flow channel, the flow speed of the air flow is slowed down, and after the flow speed of the air flow is high, the rotation speed of the power turbine rotor 032 is also high when the power turbine rotor 032 is pushed to do work, and the mechanical energy output to the outside is also high. Which enables the turboshaft engine to be cyclically adjustable. When the low-speed flying performance and the high-speed flying performance are simultaneously considered, the variable circulation turboshaft engine has good advantages. Compared with the existing turboshaft engine, the application has stronger circulation adjusting capability and task adaptability.

Although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. The novel variable-circulation turboshaft engine structure is characterized by comprising an engine outer casing, wherein a core engine, an outer duct, a power rotor (03) and a geometric adjustable mechanism (153) are arranged in the engine outer casing, an air inlet (155) and an exhaust frame (154) are arranged on the engine outer casing, the core engine comprises a fan rotor (021), a fan guide vane (121) is further arranged in the engine outer casing, and the power rotor (03) comprises a power turbine rotor (032) and a power turbine guide vane (132); the air flow enters the outer casing from the air inlet (155), the fan rotor (021) and the fan guide vane (121) divide the air flow into two air flows inside and outside, the first air flow continues to pass through the core machine, the second air flow passes through the outer duct, the geometric adjustable mechanism (153) is used for mixing the second air flow with the first air flow, the geometric adjustable mechanism (153) can adjust the flow area of the mixed air flow, and the mixed air flow flows to the power turbine guide vane (132), so that the power turbine rotor (032) is pushed to do work, and the exhaust frame (154) is used for exhausting the air flow; a transmission device is connected to the power turbine rotor (032), and the transmission device is used for outputting power.

2. The novel variable cycle scroll engine structure according to claim 1, wherein the core machine comprises two stages of rotors, which are a high-pressure rotor (01) and a low-pressure rotor (02), respectively, and the high-pressure rotor (01) comprises a high-pressure compressor rotor (011) and a high-pressure turbine rotor (012) and a connecting shaft therebetween; the fan rotor (021) belongs to the low-pressure rotor (02), and the low-pressure rotor (02) further comprises a low-pressure turbine rotor (022) and a connecting shaft for connecting the fan rotor (021) and the low-pressure turbine rotor (022).

3. The novel variable cycle scroll engine structure of claim 1, wherein said core engine comprises three or more stages of rotors.

4. A novel variable cycle scroll engine structure according to claim 2 or 3, wherein the core engine comprises a combustion chamber (04), and the structure of the combustion chamber (04) comprises a direct flow type, a return flow type or a three-stage type.

5. The novel variable-circulation turboshaft engine structure according to claim 4, wherein the compressor stator (111) is connected in the outer casing of the engine through a support plate (152) structure, and the compressor stator (111) is located between the fan rotor (021) and the combustion chamber (04).

6. The variable cycle scroll engine structure of claim 5, wherein the compressor vane and the power turbine vane (132) of the compressor stator (111) are used to adjust the flow area of the air flow.

7. The novel variable cycle scroll engine structure according to claim 1, wherein the power rotor (03) is a single-stage rotor or a double-stage rotor or a rotor with three or more stages.

8. The novel variable cycle scroll engine structure according to claim 2, wherein the high-pressure rotor (01) is a single-stage rotor or a double-stage rotor or a rotor with three or more stages.

9. The novel variable cycle scroll engine structure according to claim 2, wherein the low pressure rotor (02) is a single stage rotor or a double stage rotor or a rotor of three or more stages.

10. The novel variable cycle scroll engine structure of claim 1, wherein the transmission is a spline (033) or a membrane disc.

11. The novel variable cycle scroll engine structure of claim 1, wherein said fan rotor (021) is a single stage rotor or a double stage rotor.