Axial flow turbine with inner ducted fan

Abstract

According to the axial flow turbine with the inner duct fan, in the axial flow turbine, a turbine blade disc is of a symmetrical structure relative to the central axis, turbine rotor blades extend in the radial direction from the turbine blade disc, turbine gas channels are distributed in the turbine rotor blades, inner duct air flow channels are distributed in the turbine blade disc, and the inner duct fan is arranged in the inner duct air flow channels. At least one inner ducted fan blade extends from the turbine bladed disc to form a cooling air flow in the inner ducted air flow channel, the temperature of the cooling air flow being lower than that of fuel gas in the turbine fuel gas channel.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to an axial turbine with an internal fan. Background Technology

[0002] The existing turbine rotor is one of the core components of a jet engine. Its function is to absorb the kinetic and thermal energy of the high-temperature gas generated in the engine combustion chamber and convert it into the mechanical energy of the main shaft to drive the compressor to work and provide compressed air to the combustion chamber, thereby maintaining the engine's Brayton cycle.

[0003] The existing turbine design equipped with a ducted fan is the main technical solution adopted for rear-mounted propfan engines. This design has a connecting structure at the tip of the turbine rotor blades, and a full ring of propfan blades arranged outside the turbine rotor blades to generate engine thrust. However, due to the presence of the propfan, the overall rotor diameter is large, generating huge centripetal tensile stress during operation, which places high demands on the design and manufacturing of the turbine disk. At the same time, due to the large diameter, the rotor speed is strictly limited, and the turbine blades located at the smaller diameter have lower operating efficiency. The open rotor of the propfan also generates a lot of noise, which has a significant impact on surrounding personnel and the environment.

[0004] The information disclosed in the background section is only intended to enhance the understanding of the background of the present invention, and therefore may contain information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0005] To address the shortcomings or defects of the existing technology, an axial flow turbine with an internal duct fan is provided. The internal duct fan blades generate high-pressure cold air, producing a certain amount of thrust and offsetting part of the axial force on the turbine rotor. Simultaneously, a low-temperature airflow is formed at the blade root of the turbine rotor, cooling the turbine disk. The structure is compact, fully utilizes the space of the turbine disk core, and can provide cooling air for the turbine disk and the structure behind it.

[0006] The objective of this invention is achieved through the following technical solutions.

[0007] An axial turbine with an internal fan includes, The turbine bladed disk has a symmetrical structure with respect to its central axis. Turbine rotor blades, which extend radially from the turbine disk. Turbine gas passages, which are distributed along the turbine rotor blades, The internal airflow channels are distributed within the turbine disk. At least one inner duct fan blade extends from the turbine disk to create a cooling airflow in the inner duct airflow passage at a temperature lower than that of the gas in the turbine gas passage.

[0008] In the axial turbine with an internal duct fan, the internal duct fan blades and the turbine disk are integrally formed.

[0009] In the axial turbine with an internal duct fan, the internal duct fan blades are formed on the turbine disk by an additive manufacturing process.

[0010] In the axial turbine with an internal duct fan, the internal duct fan blades generate centrifugal force as the turbine disk rotates.

[0011] In the axial turbine with an internal duct fan, the internal duct fan blades include a blade root and a blade tip.

[0012] In the axial turbine with an internal duct fan, the turbine disk encloses the root and tip of the internal duct fan blades.

[0013] In the axial turbine with an internal duct fan, the blades of the internal duct fan constitute a centrifugal compressor.

[0014] In the axial turbine with an internal fan, the internal airflow passage is arranged independently and separately from the turbine gas passage.

[0015] In the aforementioned axial turbine with an internal channel fan, the axial turbine is connected to the tailpipe of a gas generator at one end of the internal channel airflow passage, and to a generator at the other end of the internal channel airflow passage.

[0016] In the axial flow turbine with an internal fan, the axial flow turbine with an internal fan has a centrally symmetrical structure.

[0017] Compared with the prior art, the beneficial effects of this invention are as follows: This invention, featuring an axial-flow turbine with an internal fan, fully utilizes the space at the center of the turbine rotor disk, resulting in a very compact overall structure. High-pressure, cold air is generated by a centrifugal compressor, producing a certain amount of thrust and offsetting part of the axial force on the turbine rotor. The low-temperature airflow formed by the high-pressure cold air circulation cools the roots of the turbine rotor blades and the disk. Excess cold air can continue to flow backward, shielding downstream components from the influence of high-temperature combustion gases and providing cooling air to those components.

[0018] The description provided is merely an overview of the technical solution of this invention. In order to make the technical means of this invention clearer and more understandable, so that those skilled in the art can implement it according to the contents of the specification, and to make the described and other objects, features and advantages of this invention more obvious and understandable, specific embodiments of this invention are described below. Attached Figure Description

[0019] Various other advantages and benefits of the present invention will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. Furthermore, the same reference numerals denote the same parts throughout the drawings.

[0020] In the attached diagram: Figure 1 This is a schematic diagram of a structure according to an embodiment of the present invention; Figure 2 This is a three-dimensional structural schematic diagram according to an embodiment of the present invention; Figure 3 This is a three-dimensional structural schematic diagram from another perspective of an embodiment of the present invention.

[0021] The present invention will be further explained below with reference to the accompanying drawings and embodiments. Detailed Implementation

[0022] Specific embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While specific embodiments of the invention are shown in the drawings, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the invention and to fully convey the scope of the invention to those skilled in the art.

[0023] It should be noted that certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that different terms may be used to refer to the same component. This specification and claims do not distinguish components based on differences in terminology, but rather on differences in function. The terms "comprising" or "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising but not limited to." The following descriptions are preferred embodiments for carrying out the invention; however, these descriptions are for the purpose of understanding the general principles of the specification and are not intended to limit the scope of the invention. The scope of protection of this invention is determined by the appended claims.

[0024] To facilitate understanding of the embodiments of the present invention, the following will provide further explanation and description with reference to the accompanying drawings and several specific embodiments, and the accompanying drawings do not constitute a limitation on the embodiments of the present invention.

[0025] To better understand, such as Figures 1 to 3As shown, an axial turbine with an internal fan includes, The turbine disk 203 has a symmetrical structure with respect to its central axis. Turbine rotor blades 201 extend radially from the turbine disk 203. Turbine gas passage 102 is distributed on the turbine rotor blades 201. The internal airflow channel 101 is distributed within the turbine disk 203. At least one inner duct fan blade 202 extends from the turbine disk 203 to form a cooling airflow in the inner duct airflow passage 101 at a temperature lower than that of the gas in the turbine gas passage.

[0026] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct fan blades 202 and the turbine disk 203 are integrally formed.

[0027] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct fan blades 202 are formed on the turbine disk 203 via an additive manufacturing process.

[0028] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct fan blades 202 generate centrifugal force as the turbine disk 203 rotates.

[0029] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct fan blade 202 includes a blade root and a blade tip.

[0030] In a preferred embodiment of the axial turbine with an internal duct fan, the turbine disk 203 encloses the root and tip of the internal duct fan blades 202.

[0031] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct fan blades 202 constitute a centrifugal compressor.

[0032] In a preferred embodiment of the axial turbine with an internal duct fan, the internal duct airflow passage 101 and the turbine gas passage 102 are arranged independently and separately.

[0033] The turbine is a rotating structure. The gas passage 102 is an annular passage formed by the turbine blades 201. The gas flows from left to right in the cross-sectional view. The turbine blade tip, i.e. the point of maximum rotation radius, has a turbine casing to form a closed passage.

[0034] The internal airflow channel 101 is an annular channel formed by the individual internal fan blades 202. Its diameter is smaller than that of the gas passage 102, so the two channels are independent of each other and the airflow does not intersect.

[0035] In a preferred embodiment of the axial turbine with an internal duct fan, the axial turbine is connected to the gas generator tailpipe at the intake end of the internal duct airflow channel 101, and the axial turbine is connected to the generator at the outlet end of the internal duct airflow channel 101.

[0036] In a preferred embodiment of the axial turbine with an internal fan, the axial turbine with an internal fan has a centrally symmetrical structure.

[0037] In one embodiment, the axial turbine with an internal fan is a component of a jet engine.

[0038] In one embodiment, an inner duct fan is provided inside the turbine rotor blades to form a low-temperature airflow. An inner duct centrifugal fan blade 202 is positioned at the center of the disk, forming an inner duct airflow channel 101. This channel is located inside the turbine gas passage 102. The turbine disk 203 encloses the root and tip of the inner duct fan blade, improving fan efficiency and bearing the centrifugal force generated by the rotation of the turbine rotor blades 201 and the inner duct fan blades. Since the inner duct fan blades significantly increase the stress level at this location, the blade design is constrained based on performance at reduced speeds. The inner duct fan blades cannot be manufactured using traditional casting processes; therefore, the blade design is adjusted according to the characteristics of additive manufacturing, allowing the entire disk to be manufactured using additive manufacturing.

[0039] The basic principles of this application have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this application are merely examples and not limitations, and should not be considered as essential features of each embodiment of this application. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the application to the necessity of employing the aforementioned specific details for implementation.

[0040] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this application to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. An axial turbine with an internal fan, characterized in that, It includes, The turbine bladed disk has a symmetrical structure with respect to its central axis. Turbine rotor blades, which extend radially from the turbine disk. Turbine gas passages, which are distributed along the turbine rotor blades, The internal airflow channels are distributed within the turbine disk. At least one inner duct fan blade extends from the turbine disk to create a cooling airflow in the inner duct airflow passage at a temperature lower than that of the gas in the turbine gas passage.

2. The axial turbine with an internal fan as described in claim 1, characterized in that, Preferably, the inner fan blades and the turbine disk are integrally formed.

3. The axial turbine with an internal fan as described in claim 1, characterized in that, The internal fan blades are formed on the turbine disk using an additive manufacturing process.

4. The axial turbine with an internal fan as described in claim 1, characterized in that, The blades of an internal fan include the blade root and the blade tip.

5. The axial turbine with an internal fan as described in claim 4, characterized in that, The turbine disk encloses the root and tip of the inner duct fan blades.

6. The axial turbine with an internal fan as described in claim 1, characterized in that, The internal fan blades constitute a centrifugal compressor.

7. The axial turbine with an internal fan as described in claim 1, characterized in that, The axial turbine with an internal fan is a centrally symmetrical structure.

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