CN-119435140-B - Axial unloading closed centripetal oil-gas turbine

Abstract

The invention relates to the field of aeroengine power systems, and provides an axially unloading closed centripetal oil-gas turbine, which comprises a turbine movable blade disc (4), a turbine outer cover plate (1), a back component and a plurality of turbine stationary blades (3), wherein the turbine movable blade disc comprises a plurality of moving blades which are spaced from each other to form a plurality of flow channels, the turbine outer cover plate (1) is covered on one side of the moving blades of the turbine movable blade disc (4), the back component is arranged on one side of the turbine movable blade disc (4) far away from the turbine outer cover plate (1), the plurality of turbine stationary blades (3) are arranged at the peripheral edge of the turbine movable blade disc (4) and are configured to guide airflow to enter the flow channels of the turbine movable blade disc (4), and through holes (41) except for shaft holes are formed in the center of the turbine movable blade disc (4) and are configured to enable one side of the back component to be communicated with the outlet side of the turbine movable blade disc (4). The axial unloading closed centripetal oil-gas turbine can reduce the total axial force of the centripetal turbine, prolong the service life of the bearing and improve the operation safety of the whole machine.

Inventors

• DONG BENSI
• XU GUOQIANG
• PENG XIUDONG
• ZHOU JIANJUN
• REN YONGXIANG
• LIANG YIQIANG
• LI HONGLIAN
• SUN JINGCHUAN

Assignees

• 北京航空航天大学
• 中国航发沈阳发动机研究所

Dates

Publication Date

20260508

Application Date

20241113

Claims (5)

1. 1. An axially unloaded closed centripetal oil and gas turbine, said oil and gas turbine comprising: A turbine rotor disk (4) including a plurality of rotor blades spaced apart from each other to form a plurality of flow passages configured such that a circumference Xiang Qiliu entering from an edge of the turbine rotor disk (4) flows through the rotor blades and then flows out axially from a center of the turbine rotor disk (4); a turbine outer cover plate (1) which covers one side of the moving blades of the turbine moving blade disc (4); a back assembly arranged on the side of the turbine rotor disk (4) remote from the turbine outer cover plate (1), and A plurality of turbine vanes (3) disposed at an outer peripheral edge of the turbine blade disk (4) configured to direct an airflow into a flow passage of the turbine blade disk (4), The oil-gas turbine further comprises a turbine wheel cover (2), wherein the turbine wheel cover (2) is positioned between the moving blades of the turbine movable blade disc (4) and the turbine outer cover plate (1), and is covered on the moving blades of the turbine movable blade disc (4) so that the plurality of flow channels are closed at one side; Wherein the center of the turbine rotor blade disc (4) is provided with a plurality of through holes (41) except the shaft holes, the through holes (41) are provided, the cross section of each through hole (41) perpendicular to the axial direction of the oil gas turbine is elliptical, the through holes (41) are configured to enable one side of the back component to be communicated with the outlet side of the turbine rotor blade disc (4), the through holes (41) are configured to enable the through holes (41) to twist along the circumferential direction of the turbine rotor blade disc (4) in the process of extending from the side close to the back component to the outlet side of the turbine rotor blade disc (4), and the twisting directions of the through holes (41) are the same, are consistent with the twisting directions of blades of the turbine rotor blade disc (4) and keep consistent with the twisting angles of the blades of the turbine rotor blade disc (4); The turbine outer cover plate (1) is provided with two bending edges, the two bending edges cover the two ends of the turbine wheel cover (2) respectively, the bending edges of the turbine outer cover plate (1) close to the turbine stator blades (3) are horizontally directed to the turbine stator blades (3), and the bending edges of the turbine outer cover plate (1) close to the outlet side of the turbine movable blade disc (4) are vertically directed to the axis of the turbine movable blade disc (4).
2. 2. The axially unloaded closed centripetal oil and gas turbine of claim 1, wherein: The turbine wheel cover (2) and the turbine movable blade disc (4) are relatively fixed, so that the turbine wheel cover (2) and the turbine movable blade disc (4) can rotate together.
3. 3. The axially unloaded closed centripetal oil and gas turbine of claim 2, wherein: A gap is formed between the turbine outer cover plate (1) and the turbine wheel cover (2), and a grate (21) is arranged in the gap.
4. 4. An axially unloaded closed centripetal oil and gas turbine according to claim 3, wherein: the grate (21) is arranged at a position close to the outlet side of the turbine rotor blade disc (4).
5. 5. An axially unloaded closed centripetal oil and gas turbine according to claim 3, wherein: The side of the turbine shroud (2) facing the turbine outer shroud (1) is provided with the grate (21), or The side of the turbine outer cover plate (1) facing the turbine wheel cover (2) is provided with the comb teeth (21), or The sides of the turbine shroud (2) and the turbine outer cover plate (1) facing each other are provided with the grate teeth (21).

Description

Axial unloading closed centripetal oil-gas turbine Technical Field The invention relates to the field of power systems of aircraft engines, in particular to an axial unloading closed centripetal oil-gas turbine. Background The hypersonic aircraft often works with the problem of 'more heat and less electricity', and in view of the fact that the lack of a rotary part which can be directly used for driving a generator to generate electricity in a scramjet engine, how to convert surplus heat into electric energy to realize continuous power supply for airborne equipment becomes a technical problem which is difficult to neglect in airborne energy management of the hypersonic aircraft. Among various thermoelectric conversion technologies, the oil-gas turbine power generation technology can utilize high-temperature high-pressure oil gas to push a rotor component in a turbine to rotate so as to output mechanical energy, and then drives a generator to generate power. When designing the oil gas turbine, considering that larger bleed air will lead to reduction of the main cycle efficiency of the engine, the turbine air inflow is restrained according to the required output power, and the oil gas turbine is expected to supply sufficient output power under the condition of smaller size and mass, so that the occupied space of the whole machine is reduced in an effort, the effective load of the hypersonic aircraft is increased, and the power generation device is ensured to provide sufficient electric quantity. At present, the selection of the oil gas turbine is mainly divided into two types, namely a centripetal turbine and an axial flow turbine, wherein the centripetal turbine does work under the action of centrifugal force and Gong's inertial force, higher power and higher efficiency can still be realized under the conditions of low air inflow and high rotating speed, and the oil gas turbine has the advantages of lighter weight, compact structure and the like, so that when the oil gas turbine is designed, a single-stage centripetal turbine scheme is adopted more. In the design process of a centripetal oil-gas turbine, the problem of axial force balance is a serious difficulty. In an aircraft, in order to avoid film boiling of fuel in a cooling channel and further to deteriorate heat transfer, and ensure good effect of fuel blending in a combustion chamber, it is generally required that the pressure in the cooling channel exceeds the critical pressure of the fuel, and because the fuel is cracked at high temperature, the pressure in the cooling channel is continuously increased, and finally the inlet pressure of an oil-gas turbine reaches 6MPa or even higher, and the pressure of cracked oil gas after expansion in a turbine can reach 1-3 MPa, under the high-pressure environment, even if the turbine is small in size, the total stress area is small, the total axial force (pointing to a front disk of the turbine) of the oil-gas turbine power generation device can reach more than 1000N, and most of the axial force is conducted to a casing through a bearing, and the service life of the bearing is greatly shortened under the condition of overload of long-time axial load, so that the operation safety of the whole aircraft is severely threatened. In summary, high absolute pressures and high loads present significant challenges to the axial force balance of the turbine, and therefore, it is necessary to design a centripetal turbine with a low total axial force. Chinese patent application CN202310600265.4 (publication No. CN117569871 a) provides a high-pressure oil-gas centripetal turbine structure taking axial force balance into consideration, which is also an application of applicant, which provides an axial unloading scheme for an open turbine, and applicant has tried to apply the centripetal turbine structure to a closed turbine in order to achieve the same effect of reducing axial force, but the two turbines have a relatively large difference, the same annular through hole is used in the center of a turbine movable blade disc, and a comb tooth is arranged at the middle diameter position of an impeller, and the test result cannot meet the requirement. For this reason, it is necessary to provide a solution specifically aimed at reducing the axial load of closed centripetal oil and gas turbines. In view of this, the present invention has been proposed. Disclosure of Invention The invention aims to at least partially overcome the defects of the prior art and provides an axial unloading closed centripetal oil-gas turbine. The invention also aims to provide an axially unloading closed centripetal oil-gas turbine, which reduces the total axial force of the centripetal turbine. The invention also aims to provide an axial unloading closed centripetal oil-gas turbine, which improves the service life of the bearing. The invention also aims to provide an axial unloading closed centripetal oil-gas turbine, which improves the operation safety