Exhaust pipe layout of asymmetrically-arranged turboprop aircraft
Through the asymmetrically arranged turboprop exhaust pipe layout, the problem of difficulty in effectively ejecting exhaust gas and recovering thrust in the prior art is solved, and better exhaust gas discharge, thrust recovery and handling performance are achieved.
Patent Information
- Application Number
- CN202411810536.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-10
- Publication Date
- 2025-03-14
AI Technical Summary
Existing turboprop aircraft exhaust pipe designs are difficult to effectively discharge engine exhaust gas, and may have an impact on the aircraft skin, while it is difficult to recover residual thrust and balance the reverse torque generated by the propeller.
The exhaust pipe layout of the turboprop aircraft is adopted with an asymmetrical arrangement. The exhaust direction of the left and right exhaust pipes is deflected backward at a certain angle along the heading direction, and the left and right exhaust pipes are set asymmetrically deflected according to the propeller rotation direction characteristics, and the outlet is beveled at a certain angle.
Effectively discharge engine exhaust gas, reduce the impact on the aircraft skin, recover part of the remaining thrust, and balance part of the propeller's countertorque, and improve aircraft handling performance and safety.
Smart Images
Figure CN119611769A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft design and relates to an asymmetrically arranged exhaust pipe layout of a turboprop aircraft. Background Art
[0002] The exhaust pipe of a turboprop aircraft is an important component of a turboprop aircraft. After the gas of the turboprop engine is discharged from the gas generator, it is almost all used to drive the power turbine. The exhaust gas produced by combustion is discharged from the exhaust pipe of the turboprop engine and then discharged through the exhaust pipe of the aircraft.
[0003] The aircraft exhaust pipe needs to be designed reasonably. It should be able to discharge the exhaust gas smoothly and avoid the exhaust gas from affecting the internal environment of the aircraft. When discharging the exhaust gas, it should also be careful to prevent the exhaust gas from blackening the fuselage skin. At the same time, it is best to be able to recover a certain amount of residual thrust. In addition, when the propeller of a propeller aircraft rotates, a reverse torque will be generated, which will affect the control balance of the aircraft. In response to the above problems, it is necessary to propose an asymmetric turboprop aircraft exhaust pipe layout that can help discharge the exhaust gas generated by the turboprop engine without having a significant impact on the aircraft skin. It can recover a certain amount of residual thrust and can balance part of the reverse torque generated by the propeller. Summary of the invention
[0004] The purpose of the present invention is to propose an asymmetrically arranged turboprop aircraft exhaust pipe layout, which can help discharge the exhaust gas generated by the turboprop engine without having a significant impact on the aircraft skin, can recover a certain amount of residual thrust, and can balance a portion of the anti-torque generated by the propeller.
[0005] The technical solution of the present invention:
[0006] An asymmetrically arranged turboprop aircraft exhaust pipe layout includes a fuselage, two left and right exhaust pipes are arranged on both sides of the fuselage, the exhaust directions of the left and right exhaust pipes are deflected backwards by a certain angle along the heading, the left and right exhaust pipes are asymmetrically arranged according to the characteristics of the propeller rotation direction, and the outlets of the left and right exhaust pipes are beveled at a certain angle.
[0007] Furthermore, the left and right exhaust pipe outlets are arranged at a certain distance from the fuselage and are deflected backward at a certain angle along the heading. The distance of the outlet from the fuselage and the deflection angle are determined by the engine exhaust flow, exhaust area and the shape of the nearby fuselage.
[0008] Furthermore, the left and right exhaust pipe inlets correspond to the outlets of the left and right engine exhaust pipes respectively, and the left and right exhaust pipe inlets are runway-shaped.
[0009] Furthermore, the left and right exhaust pipes transition from a racetrack-shaped inlet to a circular outlet, and the circular outlet areas of the left and right exhaust pipes are equal to the inlet areas of the corresponding exhaust pipes.
[0010] Furthermore, when the propeller rotates clockwise along the heading, the left exhaust pipe is deflected toward the belly of the aircraft by a certain angle, and the right exhaust pipe is deflected toward the back of the aircraft by a certain angle.
[0011] Furthermore, when the propeller rotates counterclockwise along the heading, the left exhaust pipe is deflected at a certain angle toward the back of the aircraft, and the right exhaust pipe is deflected at a certain angle toward the belly of the aircraft.
[0012] Furthermore, when the propeller rotates clockwise along the heading, the left exhaust pipe deflects 15° toward the belly of the aircraft, and the right exhaust pipe deflects 20° toward the back of the aircraft.
[0013] Furthermore, the exhaust directions of the left and right exhaust pipes are deflected 70° backwards along the heading.
[0014] Furthermore, the left and right exhaust pipe outlets are beveled at 45 degrees.
[0015] Beneficial effects of the present invention:
[0016] The present invention proposes an asymmetrical arrangement of turboprop aircraft exhaust pipe layout, which can discharge the exhaust gas generated by the engine out of the aircraft by deflecting it backward at a certain angle, and can also recover a part of the remaining thrust; by asymmetrically deflecting the left and right exhaust pipes according to the characteristics of the propeller rotation direction, it is used to balance part of the propeller anti-torque. That is, the performance of the turboprop engine and the use safety of the turboprop aircraft can be guaranteed, and the aircraft control design performance can also be improved. It can be used in the design of similar turboprop aircraft exhaust pipes, and the outlet is beveled at a certain angle to reduce the weight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 The left and right exhaust pipes of the present invention are viewed along the heading Figure 1 ;
[0018] Figure 2 A top view of the left and right exhaust pipes of the present invention;
[0019] Figure 3 The left and right exhaust pipes of the present invention are viewed along the heading Figure 2 ;
[0020] Among them, 1. exhaust pipe inlet, 2. exhaust pipe outlet, 3. exhaust pipe. DETAILED DESCRIPTION
[0021] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.
[0022] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.
[0023] An embodiment of the present invention proposes an asymmetrically arranged exhaust pipe layout for a turboprop aircraft, comprising a fuselage, wherein two left and right exhaust pipes are arranged on both sides of the fuselage, the exhaust directions of the left and right exhaust pipes are deflected backward at a certain angle along the heading, the left and right exhaust pipes are asymmetrically arranged according to the characteristics of the propeller rotation direction, and the outlets of the left and right exhaust pipes are beveled at a certain angle.
[0024] Among them, the left and right exhaust pipe outlets are set at a certain distance from the fuselage and deflected backward at a certain angle along the heading. The distance of the outlet from the fuselage and the deflection angle are determined by the engine exhaust flow, exhaust area and the shape of the nearby fuselage.
[0025] The left and right exhaust pipe inlets correspond to the outlets of the left and right engine exhaust pipes respectively, and the left and right exhaust pipe inlets are runway-shaped.
[0026] Among them, the left and right exhaust pipes transition from a runway-shaped inlet to a circular outlet, and the circular outlet areas of the left and right exhaust pipes are equal to the inlet areas of the corresponding exhaust pipes.
[0027] Among them, when the propeller rotates clockwise along the heading, the left exhaust pipe deflects a certain angle toward the belly of the aircraft, and the right exhaust pipe deflects a certain angle toward the back of the aircraft. When the propeller rotates counterclockwise along the heading, the left exhaust pipe deflects a certain angle toward the back of the aircraft, and the right exhaust pipe deflects a certain angle toward the belly of the aircraft.
[0028] A second embodiment of the present invention is:
[0029] Combination Figure 1-Figure 3The present invention determines the layout form of the aircraft exhaust pipe according to the engine use requirements and the overall layout requirements of the aircraft. The inlet and shape are determined by the engine exhaust pipe, that is, the outlet of the engine exhaust pipe is the inlet of the aircraft exhaust pipe (runway type). The outlet of the aircraft exhaust pipe is set at a certain distance from the fuselage and deflected backward at a certain angle. The distance of the outlet from the fuselage and the deflection angle are determined by the engine exhaust flow, exhaust area and the shape of the nearby fuselage. The outlet of the present invention is deflected backward by 70°. The outlet shape is a circle equal to the inlet area. The center of the aircraft exhaust pipe outlet is deflected upward or downward at a certain angle relative to the inlet center. The deflection angle and deflection direction are affected by the propeller rotation direction, propeller speed and the like. In the present invention, the aircraft propeller rotates clockwise (along the heading). In the present invention, in order to offset the counter-torque generated by the rotation of part of the propeller, the left exhaust pipe is deflected downward by 15°, and the right exhaust pipe is deflected upward by 20°. The aircraft exhaust pipe pipeline transitions from the runway shape of the exhaust pipe inlet to the circular outlet along the center line, and the outlet is beveled by 45°.
[0030] The present invention discharges the exhaust gas generated by the engine out of the aircraft by a design that deflects backwards at a certain angle, and can also recover a part of the remaining thrust; by asymmetrically deflecting the left and right exhaust pipes according to the characteristics of the propeller rotation direction, it is used to balance part of the propeller anti-torque. This ensures the performance of the turboprop engine and the use safety of the turboprop aircraft, and can also improve the aircraft control design performance. It can be used in the design of exhaust pipes similar to turboprop aircraft, and the outlet is beveled at a certain angle to reduce the weight of the aircraft.
[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.
Claims
1. An asymmetrical turboprop aircraft exhaust pipe layout, comprising a fuselage, wherein two left and right exhaust pipes are arranged on both sides of the fuselage, characterized in that: The exhaust directions of the left and right exhaust pipes are deflected backwards at a certain angle along the heading, the left and right exhaust pipes are asymmetrically arranged according to the characteristics of the propeller rotation direction, and the outlets of the left and right exhaust pipes are beveled at a certain angle.
2. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 1, characterized in that: The left and right exhaust pipe outlets are set at a certain distance from the fuselage and deflected backward at a certain angle along the heading. The distance of the outlet from the fuselage and the deflection angle are determined by the engine exhaust flow, exhaust area and the shape of the nearby fuselage.
3. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 1, characterized in that: The left and right exhaust pipe inlets correspond to the outlets of the left and right engine exhaust pipes respectively, and the left and right exhaust pipe inlets are runway-shaped.
4. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 3, characterized in that: The left and right exhaust pipes transition from a racetrack-shaped inlet to a circular outlet, and the circular outlet areas of the left and right exhaust pipes are equal to the inlet areas of the corresponding exhaust pipes.
5. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 1, characterized in that: When the propeller rotates clockwise along the heading, the left exhaust pipe is deflected toward the belly of the aircraft at a certain angle, and the right exhaust pipe is deflected toward the back of the aircraft at a certain angle.
6. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 5, characterized in that: When the propeller rotates counterclockwise along the heading, the left exhaust pipe is deflected toward the back of the aircraft at a certain angle, and the right exhaust pipe is deflected toward the belly of the aircraft at a certain angle.
7. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 5, characterized in that: When the propeller rotates clockwise along the heading, the left exhaust pipe deflects 15° toward the belly of the aircraft, and the right exhaust pipe deflects 20° toward the back of the aircraft.
8. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 1, characterized in that: The exhaust direction of the left and right exhaust pipes is deflected 70° backward along the heading.
9. The asymmetrical turboprop aircraft exhaust pipe layout according to claim 1, characterized in that: The left and right exhaust pipe outlets are beveled at 45°.