Propulsion motor with thermal protection structure and aviation hybrid power system thereof

Abstract

The invention provides a propulsion motor with a thermal protection structure and an aviation hybrid power system thereof. The propulsion motor is installed on an engine turbine shaft and located in an engine exhaust nozzle; a shell is arranged on the upper portion of the propulsion motor, an anti-radiation heat insulation structure is installed on the shell, and a heat insulation cavity is formed among the anti-radiation heat insulation structure, the shell and the propulsion motor and used for circulating low-temperature gas to cool the propulsion motor. According to the invention, heat generated by the motor can be taken away, most of radiation influence can be isolated, cooling of the motor is further enhanced by means of air-entraining cooling, the temperature of the motor is effectively reduced, and the safety of the engine is ensured.

Description

Technical Field

[0001] The present invention relates to the field of thermal protection of aviation hybrid power systems, and in particular to a propulsion motor with a thermal protection structure and an aviation hybrid power system thereof. Background Art

[0002] The aviation industry is facing increasingly stringent emission and economic requirements. Therefore, it has begun to focus on the hybrid technology needs of new configurations and new energy, and the development of hybrid aircraft engines has become a general trend.

[0003] The propulsion motor in the hybrid system has high power and generates high heat, while the allowable operating temperature of the motor generally does not exceed 200℃ (473K). Therefore, the design of the motor thermal protection scheme is very important.

[0004] At the same time, the engine is often in a high temperature and high pressure environment during actual operation. In addition to solid heat conduction and convection heat transfer between fluids and solids, there is also radiation heat transfer that cannot be ignored. Thermal radiation refers to the phenomenon of radiation energy emitted by an object due to heat. It is a phenomenon of electromagnetic wave energy transfer. During the thermal radiation process, an object will continuously emit thermal radiation into space and continuously absorb radiation. This process leads to heat transfer between objects in a radiation manner - radiation heat transfer.

[0005] Taking into account factors such as space, installation center of gravity, reliability, and maintainability, the propulsion motor of the aviation hybrid system is usually installed at the rear end of the engine main shaft, which is usually located at the rear casing and the lower part of the tail nozzle.

[0006] Affected by the high-temperature combustion gas, the wall temperature of the rear casing and tail nozzle is relatively high, generally reaching a high temperature of more than 1000 K. Therefore, in some high-temperature conditions, the radiated heat from the tail nozzle to the propulsion motor cannot be ignored, which can easily cause the motor temperature to rise sharply, leading to increased temperature gradients, stress concentration and other safety threats.

[0007] In the actual operation of the engine, in addition to the high temperature problem caused by the large heat generation of the propulsion motor, the radiation effect of high-temperature components on it cannot be ignored. Especially under large working conditions, when the temperature difference between the two is large, the radiation heat from the high-temperature wall will cause the motor to heat up rapidly, causing safety problems.

[0008] Currently, the thermal protection scheme for propulsion motors mainly uses lubricating oil to cool their surfaces and take away the heat generated by themselves, but does not take into account the impact of high-temperature components on their radiation. In order to prevent the adverse effects of thermal radiation, the inventors of this application have designed a propulsion motor with a thermal protection structure and an aviation hybrid power system thereof. Summary of the invention

[0009] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the lubricating oil only cools the heat generated by the propulsion motor itself without considering the influence of the high-temperature components on its radiation, and to provide a propulsion motor with a thermal protection structure and an aviation hybrid power system thereof.

[0010] The present invention solves the above technical problems through the following technical solutions:

[0011] A propulsion motor with a heat protection structure is used in an aviation hybrid power system, wherein the propulsion motor is mounted on an engine turbine shaft and is located in the engine tail nozzle;

[0012] A shell is arranged on the upper part of the propulsion motor, and a radiation-proof heat-insulating structure is installed on the shell. An insulation cavity is formed between the radiation-proof heat-insulating structure, the shell and the propulsion motor for circulating low-temperature gas to cool the propulsion motor.

[0013] According to an embodiment of the present invention, the propulsion motor is immersed in lubricating oil, and the surface of the propulsion motor is cooled by the lubricating oil.

[0014] According to an embodiment of the present invention, the shell is a metal shell.

[0015] According to an embodiment of the present invention, the radiation protection and heat insulation structure includes a radiation protection plate and a heat insulation layer, and the radiation protection plate is wrapped outside the heat insulation layer to isolate high-temperature radiation.

[0016] According to an embodiment of the present invention, the thermal insulation layer is made of ceramic fiber, and the thermal insulation layer wraps the entire shell.

[0017] According to an embodiment of the present invention, the two ends of the shell after the heat insulation layer wraps around the shell are fixed by fixing parts.

[0018] According to an embodiment of the present invention, an air inlet is provided on the shell, and the air inlet is located at the heat insulation cavity and is used to introduce low-temperature gas for cooling.

[0019] According to one embodiment of the present invention, the low-temperature gas is introduced by a compressor and performs flat plate heat exchange with the propulsion motor.

[0020] The present invention also provides an aviation hybrid power system, which is characterized in that the aviation hybrid power system includes a propulsion motor with a thermal protection structure as described above.

[0021] The positive and progressive effects of the present invention are:

[0022] The propulsion motor and aviation hybrid power system of the present invention have a thermal protection structure, which can isolate most of the radiation effects while taking away the heat generated by the motor itself. The bleed air cooling measure further strengthens the cooling of the motor, effectively reduces the temperature of the motor, and ensures the safety of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0024] Figure 1 Schematic diagram of the installation position of the engine propulsion motor.

[0025] Figure 2 It is a schematic structural diagram of a propulsion motor with a thermal protection structure according to the present invention.

[0026] Figure 3 It is a schematic diagram of the radiation protection and heat insulation structure in the propulsion motor with a thermal protection structure of the present invention.

[0027] [Reference Signs]

[0028] Engine fan 10

[0029] Engine compressor 20

[0030] Engine combustion chamber 30

[0031] Engine Turbine 40

[0032] Engine tail nozzle 50

[0033] Propulsion motor 60

[0034] Engine turbine shaft 41

[0035] Housing 70

[0036] Radiation insulation structure 80

[0037] Insulation cavity A

[0038] Radiation protection board 81

[0039] Insulation layer 82

[0040] Air Inlet 71

[0041] Cryogenic gas B DETAILED DESCRIPTION

[0042] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0043] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0044] Furthermore, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the present invention specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this document.

[0045] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings connoted by each term.

[0046] like Figure 1 As shown, the aviation hybrid power system includes an engine fan 10, an engine compressor 20, an engine combustion chamber 30, an engine turbine 40, an engine tail nozzle 50 and a propulsion motor 60 (a rotating motor for providing propulsion power) connected in sequence. The propulsion motor 60 is installed on the engine tail nozzle 50.

[0047] In the design of thermal management (the process of regulating and controlling the temperature of an object by means of heating or cooling) of existing hybrid power system propulsion motors, the main consideration is the problem of the large amount of heat generated by the motor itself, and internal and external oil cooling is used to cool it. However, during the actual operation of the engine, the high temperature environment cannot be ignored, the radiation heat exchange is large, and the temperature rise caused by radiation cannot be ignored.

[0048] If no protective measures are taken, the temperature of the motor and lubricating oil will rise at the same time, affecting the safety of the engine. Therefore, the present application proposes a cooling solution that effectively isolates the radiation effect, further reduces the operating temperature of the motor and improves safety.

[0049] For two metal walls with high temperatures and large temperature differences, the radiation heat transfer between them cannot be ignored. The tail nozzle area is exposed to the mainstream gas, and its wall temperature is close to the gas temperature. The motor is installed at a low radius position at the rear end of the engine main shaft, close to the secondary flow temperature, and the temperature difference between the two is large. If there are no special protective measures and only lubricating oil is used to cool it, under the influence of high temperature radiation, it is impossible to avoid a sharp increase in the temperature of the motor and lubricating oil, which is very likely to cause safety problems.

[0050] like Figure 2 and Figure 3 As shown, the present invention discloses a propulsion motor with a heat protection structure for use in an aviation hybrid power system. The propulsion motor 60 is mounted on the engine turbine shaft 41 and is located in the engine tail nozzle 50 (such as Figure 1 shown).

[0051] A housing 70 is provided on the upper part of the propulsion motor 60. After the propulsion motor 60 is installed, a radiation-proof heat-insulating structure 80 is installed on the housing 70. A heat-insulating cavity A is formed between the radiation-proof heat-insulating structure 80, the housing 70 and the propulsion motor 60 for circulating low-temperature gas to cool the propulsion motor 60.

[0052] Preferably, the propulsion motor 60 is immersed in lubricating oil, and the surface of the propulsion motor 60 is cooled by the lubricating oil.

[0053] Furthermore, the housing 70 is preferably a metal housing. A layer of metal housing is designed at a certain distance from the propulsion motor 60 to form a heat insulation cavity A, and a heat insulation material is wrapped outside the housing 70, and the heat insulation material is mainly composed of ceramic fiber and a metal layer.

[0054] In addition, the radiation protection and heat insulation structure 80 preferably includes a radiation protection plate 81 and a heat insulation layer 82, and the radiation protection plate 81 is wrapped outside the heat insulation layer 82 to isolate high temperature radiation.

[0055] Preferably, the heat insulating layer 82 is made of ceramic fiber, which has low thermal conductivity and achieves a heat insulating effect. The heat insulating layer 82 wraps the entire shell 70. After the heat insulating layer 82 wraps the shell 70, both ends are fixed by fixing members. The fixing members here can be rivets or other fixed connection parts.

[0056] In addition, an air inlet 71 is provided on the housing 70, and the air inlet 71 is located at the heat-insulating cavity A, for introducing low-temperature gas B for cooling. Here, the low-temperature gas B is introduced by the compressor, and reaches the heat-insulating cavity A formed by the housing 70 and the propulsion motor 60 through the rear casing support plate, and performs flat plate heat exchange with the propulsion motor 60 immersed in lubricating oil, taking away part of the heat. This method can cool the motor wall and further reduce the working temperature of the motor.

[0057] The propulsion motor with the thermal protection structure can effectively isolate the radiation effect of the high-temperature wall surface on the motor. At the same time, the bleed air cools the propulsion motor, further taking away part of the heat generated by the motor itself, thereby improving safety.

[0058] The present invention also provides an aircraft engine, which is characterized in that the aircraft engine includes a propulsion motor with a thermal protection structure as described above.

[0059] According to the above structural description, the propulsion motor with a thermal protection structure and the aviation hybrid power system thereof of the present invention combine the following multiple schemes:

[0060] 1. Use lubricating oil to cool the motor surface.

[0061] The lubricating oil mainly cools the surface of the motor and takes away part of the heat generated by the motor itself.

[0062] Second, design a layer of metal shell at a certain distance from the surface of the motor to form a heat insulation cavity, and wrap heat insulation materials outside the shell.

[0063] The metal shell is mainly used to isolate the radiation effect of high-temperature components. The heat insulation material wrapped outside has a low thermal conductivity and can better block the heat radiated from the high-temperature wall surface.

[0064] Third, introduce low-temperature gas from the compressor into the heat insulation cavity to further cool the motor.

[0065] The low-temperature gas introduced from the compressor can better cool the motor and further reduce the temperature of the motor.

[0066] In summary, the propulsion motor with a thermal protection structure and its aviation hybrid power system of the present invention can take away the heat generated by the motor itself while isolating most of the radiation effects. The measure of air intake cooling further strengthens the cooling of the motor, effectively reducing the temperature of the motor and ensuring the safety of the engine.

[0067] The propulsion motor with a thermal protection structure solves the problem of the motor's own heat dissipation that has been traditionally concerned about, and also considers the radiation effect of the high-temperature wall surface on the motor. Heat insulation materials are laid to isolate the radiation effect of the hot side, and at the same time, air is introduced into the heat insulation cavity to strengthen the cooling, further reducing the temperature of the motor and ensuring the safety of the motor.

[0068] For those skilled in the art, the above disclosure of the invention is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the exemplary embodiments of this application.

[0069] At the same time, this application uses specific words to describe the embodiments of this application. Such as "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification is not necessarily the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0070] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus facilitate the understanding of one or more embodiments of the invention, in the foregoing description of the embodiments of this application, multiple features are sometimes grouped into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the subject matter of this application requires more features than those mentioned in the claims. In fact, the features of an embodiment are less than all the features of a single embodiment disclosed above.

[0071] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A propulsion motor with a thermal protection structure for use in an aviation hybrid power system, It is characterized in that The propulsion motor is mounted on the engine turbine shaft and is located in the engine tail nozzle; A shell is arranged on the upper part of the propulsion motor, and a radiation-proof heat-insulating structure is installed on the shell. An insulation cavity is formed between the radiation-proof heat-insulating structure, the shell and the propulsion motor for circulating low-temperature gas to cool the propulsion motor.

2. The propulsion motor with a heat protection structure according to claim 1, It is characterized in that The propulsion motor is immersed in lubricating oil, and the surface of the propulsion motor is cooled by the lubricating oil.

3. The propulsion motor with a heat protection structure according to claim 1, It is characterized in that The shell is a metal shell.

4. The propulsion motor with a heat protection structure according to claim 1, It is characterized in that The radiation-proof heat-insulating structure comprises a radiation-proof plate and a heat-insulating layer, wherein the radiation-proof plate is wrapped outside the heat-insulating layer to isolate high-temperature radiation.

5. The propulsion motor with a heat protection structure according to claim 4, It is characterized in that The heat insulation layer is made of ceramic fiber, and the heat insulation layer wraps the entire shell.

6. The propulsion motor with a heat protection structure according to claim 5, It is characterized in that After the heat insulation layer wraps around the shell, both ends are fixed by fixing parts.

7. The propulsion motor with a heat protection structure according to claim 1, It is characterized in that An air inlet is provided on the shell and is located at the heat-insulating cavity for introducing low-temperature gas for cooling.

8. The propulsion motor with a heat protection structure according to claim 7, It is characterized in that The low-temperature gas is introduced by the compressor and performs plate heat exchange with the propulsion motor.

9. An aviation hybrid power system, It is characterized in that The aviation hybrid power system includes a propulsion motor with a thermal protection structure as described in any one of claims 1-8.

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