CN113202564A

CN113202564A - Bladeless turbine of radial work based on pressure differential

Info

Publication number: CN113202564A
Application number: CN202110662592.3A
Authority: CN
Inventors: 罗云奎
Original assignee: Shenzhen Puban Technology Co ltd
Current assignee: Shenzhen Puban Technology Co ltd
Priority date: 2021-06-15
Filing date: 2021-06-15
Publication date: 2021-08-03

Abstract

The invention discloses a radial-working bladeless turbine based on pressure difference, wherein a plurality of disc bodies are coaxially stacked, each disc body is provided with a radially-extending spiral channel, each radially-extending spiral channel is provided with a first width and a first height, each spiral channel of each disc is provided with a working medium inlet, each working medium inlet is configured to receive high-pressure working medium gas at the center of each disc, the gas is released from an outlet at the outermost diameter position of each disc body in the tangential direction of the disc bodies, the spiral channels of each disc body are configured to gradually release the pressure of the gas through multiple rotations of the spirals, the temperature and the pressure of the working medium gas are gradually reduced through the multiple rotations of the spirals between the adjacent disc bodies, and therefore the rotation direction of the disc bodies is controlled to rotate around a shaft body in the opposite direction of the rotation of the high-pressure working medium gas through the pressures. The invention obtains the bladeless turbine engine which has high energy conversion efficiency and effectively prevents overheating deformation through the design.

Description

Bladeless turbine of radial work based on pressure differential

Technical Field

The invention relates to the technical field of turbines, in particular to a bladeless turbine working radially based on pressure difference.

Background

A turbine engine is an engine that uses a rotating machine member to draw kinetic energy from a fluid passing through it, and has extremely wide application in various fields such as people's life, industrial production, national defense, aerospace, and the like. The turbine engines commonly used at present are bladed turbine engines, including water turbines, wind turbines, steam turbines, gas turbines, and the like. The turbine engine with fan blades generates power by utilizing fluid to impact the blades to rotate, the energy conversion efficiency of the turbine engine based on the working principle is not high, and the blades are easy to break or damage by the direct impact of the fluid, especially long and narrow blades. Based on the above-mentioned problems with the bladed turbine engine, the great inventor, nigula, tesla, proposed a raw model of an un-bladed turbine engine driven by fluid shear forces based on boundary layer effects, which theoretically has very high energy conversion efficiency and long service life. However, a series of subsequent experiments prove that the flabellless turbine engine has two serious problems that the disk plate is very easily stretched and twisted under the action of strong centrifugal force when the rotor runs at ultrahigh speed, and the larger the diameter of the disk plate is, the higher the twisting degree is; secondly, the disk sheet is very easy to overheat but not be cooled and protected due to unavoidable frictional heat generation in the flowing process of the fluid, the disk sheet is quickly thermally deformed to cause damage, and the phenomenon of thermal deformation is more serious when the temperature of the fluid is higher; the concept of such fladless turbine engines has thus far not been practical for over a century. In addition to the selection of advanced processing materials, the internal structure of the engine should be improved to solve the above two problems, so that the flabellless turbine engine can be actually used in the future.

The present invention forces high pressure gas through a number of turns of long and shallow helical channels by using a novel turbine design based on pressure differential, the gas working in the long helical channel of set width and set height, and a gradual near linear pressure drop along the length of the helix occurs when the helix is rotated at an appropriate angular velocity. The adiabatic expansion of the gas occurs progressively as the gas rotates in a spiral, making the process substantially isentropic.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. To this end, the invention discloses a radial-working bladeless turbine based on pressure difference, wherein a plurality of disc bodies are coaxially stacked, each disc body is provided with a radially-extending spiral channel, each radially-extending spiral channel has a first width and a first height, each spiral channel of each disc is provided with a working medium inlet, each working medium inlet is configured to receive high-pressure working medium gas at the center of each disc, the gas is released from an outlet at the outermost diameter position of each disc body in the tangential direction of the disc bodies, the spiral channel of each disc body is configured to gradually release the pressure of the gas through multiple rotations of the spiral, the temperature and the pressure of the working medium gas are gradually reduced through multiple rotations of the spiral between the adjacent disc bodies, and therefore the rotation direction of the disc bodies is controlled to rotate around the shaft body in the opposite direction of the rotation of the high-pressure working medium gas through the pressure.

Furthermore, each disk body is a solid disk body, the shaft body is a hollow shaft body, each spiral channel is provided with a plurality of turns engraved on the corresponding disk body, and the working medium inlet and the working medium outlet of each spiral channel on the disk body are provided with different phase angles from those of the spiral channels on other disk bodies.

Furthermore, the main inlet of the working medium gas is perpendicular to the disc bodies and is arranged along the direction of the shaft body, the main inlet of the working medium gas is provided with an opening structure, the opening is used as a bearing, and the plurality of disc bodies can smoothly rotate around the main inlet of the working medium gas.

Still further, the first width is 0.68 centimeters and the first height is 0.12 centimeters.

Still further, the first width is less than 0.8 centimeters and the first height is less than 0.4 centimeters.

Still further, the radially operating vaneless turbine has an auxiliary working fluid inlet extending through the central bottom circular surface of the cylindrical housing and for providing auxiliary pressurized working fluid to the working fluid inlets of the helical channels of the plurality of discs, thereby creating a pressure differential with the main inlet of the working fluid gas to balance the pressure of the system.

The invention has the advantages that the invention has obvious beneficial effects, high-pressure gas is forced to pass through a plurality of turns of long spiral channels and shallow spiral channels by adopting a novel turbine design based on pressure difference, the gas works in the long spiral channels with set width and set height, and when the spiral line rotates at proper angular speed, the pressure drop gradually approaching to linearity can occur along the length of the spiral line. The adiabatic expansion of the gas occurs progressively as the gas rotates in a spiral, making the process substantially isentropic.

Drawings

The invention will be further understood from the following description in conjunction with the accompanying drawings. The components in the figures are not necessarily to scale, emphasis instead being placed upon illustrating the principles of the embodiments. In the drawings, like reference numerals designate corresponding parts throughout the different views.

FIG. 1 is a flow chart of the operation of the radial vaneless turbine of the present invention;

FIG. 2 is a block diagram of a radial vaneless turbine of the present invention.

Detailed Description

Example one

As shown in fig. 1, the present embodiment provides a pressure difference-based radially operating bladeless turbine in which a plurality of disks are coaxially stacked, each disk being provided with a radially extending helical channel, said radially extending spiral channels having a first width and a first height, said spiral channels of each of said disks having a working fluid inlet configured to receive high pressure working fluid gas at the center of said disk, wherein, the gas is released from the outlet at the outermost diameter position of the disc body in the tangential direction of the disc bodies, the spiral channel of each disc body is constructed to gradually release the pressure of the gas through the multiple rotation of the spiral, the temperature and the pressure of the working medium gas are gradually reduced between the adjacent disc bodies through the multiple rotation of the spiral, thereby controlling the rotation direction of the disc body to rotate around the shaft body in the opposite direction of the rotation of the high-pressure working medium gas through pressure.

Example two

The embodiment provides a pressure difference-based bladeless turbine working radially, wherein a plurality of disc bodies are stacked coaxially, each disc body is provided with a radially extending spiral channel, each radially extending spiral channel is provided with a first width and a first height, each spiral channel of each disc is provided with a working medium inlet, each working medium inlet is configured to receive high-pressure working medium gas at the center of each disc, the gas is released from an outlet at the outermost diameter position of each disc body in the tangential direction of the disc bodies, the spiral channels of each disc body are configured to gradually release the pressure of the gas through multiple rotations of the spirals, the temperature and the pressure of the working medium gas are gradually reduced through the multiple rotations of the spirals between adjacent disc bodies, and therefore the rotation direction of the disc bodies is controlled through the pressure to rotate around the shaft body in the opposite direction of the rotation of the high-pressure working medium gas. The radial-working bladeless turbine also has an auxiliary working medium inlet which extends through the circular surface at the central bottom of the cylindrical shell and is used for providing auxiliary pressurized working medium for the working medium inlets of the spiral channels of the plurality of disc bodies so as to form a pressure difference with the main inlet of the working medium gas to balance the pressure of the system.

And still further, the first width is designed to be less than 0.8 cm in this embodiment and the first height is designed to be less than 0.4 cm in this embodiment.

In this embodiment, as shown in FIG. 2, high pressure and high temperature working fluid gas continues to flow down the rotating shaft (not shown) and 11 is the gas inlet of the disk, which advantageously acts as a gas bearing, although some gas may leak at the connection of the gas inlet and the rotating shaft. The gas spin axes are closed at the other end and gas enters the working enclosure (not shown) of the disk at inlet 12. Each disc has a cut helical channel 12, the circular symmetry of the helix balancing the weight of the disc. In addition, gas is ejected at the outlet on opposite sides of the two disks. This balanced gas injection makes the turbine rotate smoothly.

It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.

Although the invention has been described above with reference to various embodiments, it should be understood that many changes and modifications may be made without departing from the scope of the invention. It is therefore intended that the foregoing detailed description be regarded as illustrative rather than limiting, and that it be understood that it is the following claims, including all equivalents, that are intended to define the spirit and scope of this invention. The above examples are to be construed as merely illustrative and not limitative of the remainder of the disclosure. After reading the description of the invention, the skilled person can make various changes or modifications to the invention, and these equivalent changes and modifications also fall into the scope of the invention defined by the claims.

Claims

1. A bladeless turbine working radially based on pressure difference is characterized in that a plurality of disk bodies are coaxially stacked, each disk body is provided with a radially extending spiral channel, each radially extending spiral channel is provided with a first width and a first height, each spiral channel of each disk is provided with a working medium inlet, each working medium inlet is configured to receive high-pressure working medium gas at the center of each disk, the gas is released from an outlet at the outermost diameter position of each disk body in the tangential direction of the disk bodies, the spiral channels of each disk body are configured to gradually release the pressure of the gas through multiple rotations of the spiral, the temperature and the pressure of the working medium gas are gradually reduced between adjacent disk bodies through multiple rotations of the spiral, and therefore the rotation direction of the disk bodies is controlled to rotate around a shaft body in the opposite direction of the rotation of the high-pressure working medium gas through the pressure.

2. The pressure differential based radially operating bladeless turbine according to claim 1, wherein each said disk is a solid disk, said shaft is a hollow shaft, and each helical channel has a plurality of turns engraved on the respective disk, said working fluid inlet and working fluid outlet of each said helical channel on a disk having a different phase angle than the helical channels on the other disks.

3. The pressure differential-based radially operating bladeless turbine according to claim 1, wherein the inlet for the working medium gas is arranged perpendicular to the disks in the axial direction, the inlet for the working medium gas has an open structure, and the opening serves as a bearing, and the disks are allowed to rotate smoothly around the inlet for the working medium gas.

4. A pressure differential based radially operating bladeless turbine according to claim 1, wherein the first width is 0.68 cm and the first height is 0.12 cm.

5. A pressure differential based radially operating bladeless turbine according to claim 1, wherein the first width is less than 0.8 cm and the first height is less than 0.4 cm.

6. A differential pressure based radially operating bladeless turbine according to claim 2, wherein the radially operating bladeless turbine further has an auxiliary working fluid inlet extending through the central bottom circular surface of the cylindrical housing and adapted to provide auxiliary pressurized working fluid to the working fluid inlets of the helical channels of the plurality of discs, thereby creating a differential pressure with the main inlet of working fluid gas to balance the system pressure.