Flow deflector device for exhaust part of helicopter engine

Abstract

The utility model provides a flow deflector device for an exhaust part of a helicopter engine, the flow deflector device comprises a shell 1, a first connecting piece 2, a flow deflector 3 and a second connecting piece 4, the shell 1 is arranged on an engine body structure of the exhaust part of the helicopter engine, and the shell 1 is an elliptical cylinder; n groups of flow deflector assemblies are arranged on the shell 1; each flow deflector assembly comprises a first connecting piece 2, a flow deflector 3 and a second connecting piece 4; the flow deflectors 3 of the flow deflector assembly are connected with the shell 1 through the first connecting piece 2 and the second connecting piece 4.

Description

Technical Field

[0001] The present invention relates to the field of helicopter engines, and in particular to a guide vane device used for an exhaust portion of a helicopter engine. Background Art

[0002] At present, the exhaust part of some helicopter engines at home and abroad adopts a sleeve-type waist-shaped structure. Figure 1 This is a schematic diagram of a conventional sleeve-shaped waist-shaped structure for the exhaust port of a helicopter engine. This structure fits directly over the engine's exhaust port, directing the high-temperature, high-speed airflow ejected by the engine into the atmosphere. However, this can easily cause excessive engine compartment temperatures, burning the fairing surface, or damaging accessories within the engine compartment. Summary of the Invention

[0003] The present application provides a guide vane device for the exhaust portion of a helicopter engine, which can effectively reduce the temperature of the engine compartment.

[0004] The technical solution of the present invention is: a guide vane device for the exhaust part of a helicopter engine, the guide vane device includes a housing 1, a first connecting piece 2, a guide vane 3, and a second connecting piece 4, wherein:

[0005] A shell 1 is provided on the body structure of the helicopter engine exhaust part, and the shell 1 is an elliptical cylinder; N groups of guide vane assemblies are provided on the shell 1, and the guide vane assemblies include a first connecting piece 2, a guide vane 3 and a second connecting piece 4; the guide vanes 3 of the guide vane assemblies are connected to the shell 1 through the first connecting piece 2 and the second connecting piece 4.

[0006] Specifically, each guide vane 3 has M long open slots to adapt to the changes in the alternating internal stress of the high-temperature and high-speed engine jet airflow.

[0007] Specifically, the direction of the long open slots on the guide vane 3 is consistent with the exhaust airflow direction of the helicopter engine.

[0008] Specifically, N groups of guide vane assemblies are evenly distributed in the housing 1 .

[0009] Specifically, the N and the M are set according to the exhaust gas cooling effect of the helicopter engine.

[0010] Specifically, the housing 1 , the first connecting piece 2 , the guide piece 3 , and the second connecting piece 4 are made of a high-temperature resistant metal material that can withstand 1000 degrees Celsius.

[0011] In summary, the present invention relates to a guide vane device for the exhaust part of a helicopter engine, and more particularly to a guide vane device for a tail nozzle of a helicopter engine, which has a structure that compensates for structural deformation and accelerates the airflow diversion speed; the high-temperature and high-speed engine jet airflow acts alternately on the shell 1, the first connecting piece 2, the guide vane 3 and the second connecting piece 4, generating alternating internal stresses between each other, and the direction of the long open grooves on the guide vane 3 is parallel to the direction of the jet airflow. When the alternating internal stress is large, the size of the open grooves on the guide vane increases, and when the internal stress is small, the size of the open grooves on the guide vane decreases, adapting to the changes in the alternating internal stress, thereby effectively avoiding the generation of fatigue cracks in a certain part of the shell 1, the first connecting piece 2, the guide vane 3 and the second connecting piece 4. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of an existing engine tail nozzle;

[0013] Figure 2 This is a schematic diagram of a guide vane device for use at an exhaust portion of a helicopter engine provided by the present invention;

[0014] Among them, 1-shell, 2-first connecting piece, 3-guide piece, 4-second connecting piece. DETAILED DESCRIPTION

[0015] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0016] See also Figure 2 The present invention provides a guide vane device for the exhaust part of a helicopter engine, comprising a housing 1, a first connecting piece 2, a guide vane 3, and a second connecting piece 4, wherein:

[0017] A shell 1 is provided on the body structure of the helicopter engine exhaust part, and the shell 1 is an elliptical cylinder; N groups of guide vane assemblies are provided on the shell 1, and the guide vane assemblies include a first connecting piece 2, a guide vane 3 and a second connecting piece 4; the guide vanes 3 of the guide vane assemblies are connected to the shell 1 through the first connecting piece 2 and the second connecting piece 4.

[0018] It should be noted that N groups can be connected to the guide vane device to speed up the high-temperature and high-speed engine jet air flow speed, play an ejection effect, and thus avoid the generation of high temperature in the engine compartment.

[0019] Preferably, each guide plate 3 has M long open slots to adapt to the changes in the alternating internal stress of the high-temperature and high-speed engine jet airflow.

[0020] More preferably, the direction of the long open slots on the guide vane 3 is consistent with the exhaust airflow direction of the helicopter engine.

[0021] Preferably, N groups of guide vane assemblies are evenly distributed in the housing 1 .

[0022] Preferably, the N and the M are set according to the exhaust cooling effect of the helicopter engine.

[0023] Preferably, the housing 1, the first connecting piece 2, the guide piece 3 and the second connecting piece 4 are made of a high-temperature resistant metal material, which can withstand 1000 degrees Celsius.

[0024] During actual operation, the guide vane device used in the exhaust part of the helicopter engine can accelerate the outflow of high-temperature and high-speed engine tail nozzle airflow, quickly discharge the high-temperature and high-speed airflow into the atmosphere, play an induced effect, and reduce the temperature in the engine compartment. According to the cooling effect requirements, multiple sets of guide vanes can be installed.

[0025] The helicopter of the present invention has a guide vane device that compensates for structural deformation and accelerates the airflow diversion speed. By arranging long open grooves on the guide vane, it can well adapt to the internal stress changes caused by the high-temperature and high-speed alternating airflow of the engine tail nozzle, and can well avoid the occurrence of fatigue cracks in any part of the guide vane device. According to structural requirements, a plurality of long open grooves can be provided.

[0026] In summary, the present invention relates to a guide vane device for the exhaust part of a helicopter engine, and more particularly to a guide vane device for a tail nozzle of a helicopter engine, which has a structure that compensates for structural deformation and accelerates the airflow diversion speed; the high-temperature and high-speed engine jet airflow acts alternately on the shell, the first connecting piece, the guide vane, and the second connecting piece, generating alternating internal stresses between each other; the long open grooves on the guide vane are parallel to the direction of the jet airflow; when the alternating internal stress is large, the size of the open grooves on the guide vane increases; when the internal stress is small, the size of the open grooves on the guide vane decreases, adapting to the changes in the alternating internal stress, thereby effectively avoiding the generation of fatigue cracks in a certain part of the shell, the first connecting piece, the guide vane, and the second connecting piece.

Claims

1. A guide vane device for the exhaust part of a helicopter engine, characterized in that: The guide plate device comprises a housing (1), a first connecting plate (2), a guide plate (3), and a second connecting plate (4), wherein: A shell (1) is provided on the body structure of the exhaust portion of a helicopter engine, wherein the shell (1) is an elliptical cylinder; N groups of guide vane assemblies are provided on the shell (1), wherein the guide vane assemblies include a first connecting piece (2), a guide vane (3) and a second connecting piece (4); and the guide vanes (3) of the guide vane assemblies are connected to the shell (1) via the first connecting piece (2) and the second connecting piece (4).

2. The wafer taping device according to claim 1, wherein: Each guide plate (3) has M long open slots to adapt to the changes in the alternating internal stress of the high-temperature and high-speed engine jet airflow.

3. The wafer taping device according to claim 1, wherein: The direction of the long open slot on the guide plate (3) is consistent with the exhaust airflow direction of the helicopter engine.

4. The wafer taping device according to claim 1, wherein: N groups of guide vane assemblies are evenly distributed in the housing (1).

5. The wafer taping device according to claim 2, wherein: The N and the M are set according to the exhaust gas cooling effect of the helicopter engine.

6. The wafer taping device according to claim 1, wherein: The housing (1), the first connecting piece (2), the guide piece (3), and the second connecting piece (4) are made of a high-temperature resistant metal material, and the high-temperature resistant metal material can withstand 1000 degrees Celsius.

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