JP2003166427A - Engine for aviation - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an engine for aviation with improved thrust and fuel consumption using outside air for oil cooling without impairing low pressure loss and ventilation flow. <P>SOLUTION: This engine 1 for aviation is constituted by an engine main body 3 composed of a compressor 13, a combustor 15, and a turbine 17 and a nacelle 5 formed at outer periphery of the engine main body 3. An outside air intake port 83 is provided on a front side in an outer cowl 77 of the nacelle 5, and an exhaust port 85 is provided in the outer cowl 77 on a rear side of the outside air intake port 83. A heat exchanger 89 for cooling oil circulating into the engine main body 3 from an oil tank 91 is provided on the halfway of an air passage 87 formed in the nacelle 5 between the outside air intake port 83 and the exhaust port 85. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

TECHNICAL FIELD The present invention relates to an aeronautical engine.

[0002]

2. Description of the Related Art Conventionally, as shown in FIG. 4, for example, an aviation engine 1 is attached to a main wing A of an airplane via a pylon B. The aviation engine 1 is a turbofan engine, and includes an engine body 3 and a nacelle (also referred to as intake cowl and fan cowl) 5 formed on the outer periphery of the engine body 3.
In the core cowl 7 of the engine body 3, a core side flow passage 9 is provided.
Are formed. A space between the core cowl 7 and the nacelle 5 serves as a bypass side flow passage 11. Then, in the core side flow passage 9, from the front side to the rear side (from the left side to the right side in FIG. 1), the compressor 13, the combustor 15, and the turbine 17 are provided.
Are arranged in order.

A rotatable fan 19 is provided in front of the compressor 13 (to the left in FIG. 1). The compressor 13 includes a low pressure compressor blade 23 installed in a plurality of rows on the outer side of the fan disk 21 and a low pressure compressor vane 25 installed in a plurality of rows on the inner side of the core side passage 9. A high pressure composed of a machine part 27, high pressure compressor blades 31 mounted in a plurality of rows on the outer side of the compressor disk 29, and high pressure compressor vanes 33 mounted in a plurality of rows on the inner side of the core side flow passage 9. It is composed of a compressor unit 35.

Further, the turbine 17 includes a high pressure turbine blade 39 mounted in a plurality of rows on the outer side of the high pressure turbine disk 37 and a high pressure turbine stationary blade mounted in a plurality of rows on the inner side of the core side passage 9. A high pressure turbine section 43 composed of 41, a low pressure turbine rotor blade 47 mounted in a plurality of rows on the outer side of the fan low pressure turbine disk 45, and a low pressure turbine static turbine mounted in a plurality of rows on the inner side of the core side passage 9. It is composed of a low pressure turbine section 51 composed of blades 49.

An inlet cone 53 is attached to the front side (left side in FIG. 1) of the fan disk 21, and a tail cone 55 is attached to the rear side (right side in FIG. 1) of the fan drive turbine disk 45. ing.

When the aeronautical engine 1 is started by the above configuration. First, the compressor disk 29 and the compressor drive turbine disk 37 mechanically directly connected to the compressor disk 29 are rotationally driven using a start-up turbine (starter) not shown. When the compressor drive turbine disk 37 rotates, the air compressed by the compressor disk 29 flows into the combustor 15.

When the rotation speed of the compressor driving turbine disk 37 or the like reaches a predetermined rotation speed, sparks for ignition are generated in the combustor 15 by the spark plug 16, and the high pressure compressor section 35 causes the spark to come out. The fuel is sprayed into the air flowing into 15 to burn the fuel.

When the fuel burns, the generated combustion gas is jetted rearward from the combustor 15, and the jetting energy thereof causes the high pressure turbine section 43 and the low pressure turbine section 51.
And are rotated.

When the high-pressure turbine section 43 and the low-pressure turbine section 51 are driven as described above, the low-pressure compression section 27 connected to the low-pressure turbine section 51 causes air outside the engine to flow from the left side in FIG. Most of the compressed air that has been sucked and compressed by the flow into the bypass-side flow path 11 side, and the remaining air is sent to the high-pressure compressor section 35 connected to the high-pressure turbine section 43, and After being compressed, it will flow into the combustor 15.

By continuously spraying the fuel into the combustor 15, the combustion gas is continuously generated, and the high-temperature combustion gas that rotates the low-pressure turbine section 51 and the bypass sidestream are generated. The air that has passed through the passage 11 is ejected to the outside of the engine to generate thrust.

In order to supply oil to the engine body 3, an oil tank 59 is provided in the nacelle 5, and an oil pump 61 and a gear box 63 are also provided. In addition, a block-type heat exchanger 65 is provided in the bypass side flow passage 11. The oil tank 59 and the oil pump 61 are connected by pipes 67 and 69, and the oil pump 61 and the block heat exchanger 65 are connected by a pipe 71. In addition, the block heat exchanger 65 and each sump chamber in the engine body 3 are connected by a pipe 73, and the oil pump 61 and each sump chamber in the engine body 3 are connected by a pipe 75.

With the above structure, when the gearbox 63 is driven to operate the oil pump 61, the oil in the oil tank 59 is sent to the block heat exchanger 65 via the pipe 67 and the pipe 71 to cool the oil. It The cooled oil is supplied to each sump chamber in the engine body 3 through the pipe 73. In addition, the oil that has become high temperature in each sump chamber in the engine body 3 is the pipe 75 and the oil pump 6.
It is returned to the oil tank 59 via 1 and the pipe 69.
By thus circulating the oil, the cooled oil is always supplied to each sump chamber in the engine body 3.

[0013]

By the way, in the conventional aviation engine 1 described above, the block-type heat exchanger 65 is provided in the bypass side flow passage 11, and the engine compressed air is used to generate the high temperature oil. Since it is cooled, the thrust and fuel consumption are deteriorated. Further, since the block heat exchanger 65 is heavy and has a large area, the weight is increased and the space is wasted.
Further, since the block heat exchanger 65 is used as the heat exchanger, there are problems that the pressure loss is large and the ventilation flow is obstructed.

In some cases, the block heat exchanger 65 may be provided in the core-side flow passage 9, but in this case as well, there are the above-mentioned problems.

The present invention has been made to solve the above-mentioned problems, and its purpose is to improve thrust and fuel efficiency by using outside air for cooling oil and to prevent low pressure loss and obstruction of ventilation flow. To provide a aviation engine that does.

[0016]

In order to achieve the above object, an aeronautical engine of the present invention according to claim 1 is formed with an engine body composed of a compressor, a combustor and a turbine, and an outer periphery of the engine body. In an aeronautical engine configured with a nacelle, an air passage formed in the nacelle between the outside air intake port and the exhaust port by providing an outside air intake port on the front side of the nacelle and an exhaust port in the nacelle. A heat exchanger for cooling the oil circulated from the oil tank to the engine body is provided in the middle of.

Therefore, after the outside air is taken in from the outside air intake port provided on the front side of the nacelle and the heat circulating from the oil tank to the engine body is cooled by the heat exchanger provided in the middle of the air passage, By being discharged from the outlet, without using engine compressed air,
By cooling the high temperature oil using the outside air, the thrust and the fuel consumption can be improved.

According to a second aspect of the present invention, there is provided an aeronautical engine comprising an engine body composed of a compressor, a combustor and a turbine, and a nacelle formed on the outer periphery of the engine body. An air intake on the front side and an exhaust on the nacelle, and a heat exchanger connected to the inside of the nacelle for cooling the oil circulating from the oil tank to the engine body. It is characterized by.

Therefore, the outside air is taken in from the outside air intake port provided on the front side of the nacelle and is circulated from the oil tank to the engine body by the heat exchanger provided inside the exhaust port provided in the nacelle. After the cooling oil is cooled, it is discharged from the discharge port, so that the high temperature oil is cooled using the outside air without using the engine compressed air, so that the thrust and the fuel consumption are improved.

The aviation engine of the present invention according to claim 3 is the aviation engine according to claim 1 or 2, wherein
The heat exchanger is a surface type heat exchanger.

Therefore, by using the surface type heat exchanger as the heat exchanger, the low pressure loss, the ventilation flow are obstructed, and the size and weight are reduced.

[0022]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will now be described in detail with reference to the drawings.

FIG. 1 is a side sectional view of an aviation engine according to the present invention, and FIG. 2 is a sectional view taken along line II-II in FIG. 1 and 2, parts that are the same as the parts described in the related art are denoted by the same reference numerals, and detailed description thereof will be duplicated, so description thereof will be omitted.

1 and 2, the nacelle 5 is composed of an outer cowl 77 and an inner cowl 79. For example, a partition wall 81 is formed between the outer cowl 77 and the inner cowl 79 on the lower side in the vertical direction in FIG. There is. An outside air intake port 83 is provided on the front side of the outer cowl 77 of the partition wall 81, and an outer cowl 77 behind the outside air intake port 83 is provided.
A discharge port 85 is provided in the. The nacelle 5 between the outside air intake port 83 and the exhaust port 85 is
A surface type heat exchanger 89 for cooling the oil is attached to the partition wall 81 inside the partition 81 and the air passage 87 formed in the outer cowl 77.

In order to supply oil to the engine body 3, an oil tank 91 is provided in the nacelle 5, and an oil pump 93 and a gear box 95 are also provided. The oil tank 91 and the oil pump 93 are connected by the pipes 97 and 99, and the oil pump 93 and the surface heat exchanger 89 are connected by the pipe 1.
It is connected with 01. Further, the surface heat exchanger 89 and the combustion chamber 15 are connected by a pipe 103, and the oil pump 93 and each sump chamber in the engine body 3 are connected by a pipe 105. .

With the above construction, when the gearbox 95 is driven to operate the oil pump 93, the oil in the oil tank 91 is sent to the surface type heat exchanger 89 via the pipe 97 and the pipe 101 to cool the oil. It
The cooled oil is supplied to each sump chamber in the engine body 3 through the pipe 103. In addition, the oil having a high temperature in each sump chamber in the engine body 3 is returned to the oil tank 91 through the pipe 105, the oil pump 93, and the pipe 99. By thus circulating the oil, the cooled oil is supplied to each sump chamber in the engine body 3.

As a result, the outside air is taken in through the outside air intake port 83 provided on the front side of the outer cowl 77 of the nacelle 5, and the surface heat exchanger 89 provided in the middle of the air passage 87 is cooled by the outside air. Since the oil circulating from the oil tank 91 to the combustion chamber 15 is constantly cooled by the surface heat exchanger 89 and then discharged from the discharge port 85, the outside air is used without using the engine compressed air. By cooling the high temperature oil, thrust and fuel consumption can be improved.

FIG. 3 shows another embodiment of FIG. In FIG. 3, the same parts as those of FIG.

3 is different from FIG. 2 in that the outer cowl 77 on the rear side of the outside air intake port 83 is provided with a discharge port 85, which is connected to the inside of the discharge port 85 to cool oil. A mold heat exchanger 89 is provided.

Thus, the outside air is taken in from the outside air intake port 83 provided on the front side of the outer cowl 77 of the nacelle 5 and connected to the inside of the exhaust port 85 provided on the outer cowl 77 on the rear side of the outside air intake port 83. Since the surface type heat exchanger 89 provided as a component is cooled by the outside air, after the oil circulating from the oil tank 91 to, for example, the shaft portion in the engine body 3 is constantly cooled by the face type heat exchanger 89, By being discharged from the discharge port 85, the high temperature oil can be cooled by using the outside air without using the engine compressed air, so that the thrust and the fuel consumption can be improved.

In FIGS. 1 and 3, the surface type heat exchanger 85 is used as the heat exchanger,
It is possible to reduce low pressure loss and obstruct the ventilation flow, and to reduce the size and weight.

The present invention is not limited to the above-described embodiment, but can be implemented in other modes by making appropriate changes.

[0033]

As can be understood from the above description of the embodiment of the invention, according to the invention of claim 1, the outside air is taken in from the outside air intake port provided on the front side of the nacelle, and the air passage is A heat exchanger provided on the way cools the oil that circulates from the oil tank to the engine body, and then discharges it from the discharge port. By cooling the engine, it is possible to improve thrust and fuel efficiency.

According to the second aspect of the present invention, the heat exchanger provided by taking in the outside air from the outside air intake port provided on the front side of the nacelle and connecting the inside of the exhaust port provided in the nacelle with the oil After the oil that circulates from the tank to the engine body is cooled, it is discharged from the discharge port, so that the high temperature oil is cooled using outside air instead of using engine compressed air, which improves thrust and fuel efficiency. Can be planned.

According to the third aspect of the present invention, by using the surface type heat exchanger as the heat exchanger, the low pressure loss and the ventilation flow can be obstructed and the size and weight can be reduced. .

[Brief description of drawings]

FIG. 1 is a side sectional view of an aircraft engine of the present invention.

FIG. 2 is a sectional view taken along line II-II in FIG.

FIG. 3 is a side sectional view of an aeronautical engine according to another embodiment, which is an alternative to FIG.

FIG. 4 is a side sectional view of a conventional aviation engine.

[Explanation of symbols]

1 Aviation engine 3 engine body 5 nacelle 7 Outer case 9 Core side flow path 11 Bypass side flow path 13 compressor 15 Combustor 17 turbine 19 fans 21 fan disk 27 Low pressure compressor section 29 Compressor disk 35 High pressure compressor section 37 High Pressure Turbine Disc 43 High-pressure turbine section 45 low pressure turbine disc 77 Outer cowl 79 Inna Cowl 81 partition 83 Outside air intake 85 outlet 87 Air passage 89 Surface type heat exchanger (heat exchanger) 91 oil tank 93 Oil pump 95 gearbox 97, 99, 101, 103, 105 Piping

Claims (3)

[Claims] 1. An aeronautical engine comprising an engine main body composed of a compressor, a combustor and a turbine, and a nacelle formed on the outer periphery of the engine main body. A discharge port is provided in the nacelle, and a heat exchanger for cooling the oil circulating from the oil tank to the engine body is provided in the air passage formed in the nacelle between the outside air intake port and the discharge port. An aviation engine characterized by being provided. 2. An aeronautical engine comprising an engine body composed of a compressor, a combustor, and a turbine, and a nacelle formed on the outer periphery of the engine body, wherein an outside air intake port is provided on the front side of the nacelle and An aeronautical engine comprising a nacelle provided with a discharge port, and a heat exchanger connected to the inside of the discharge port for cooling oil circulating from the oil tank to the engine body. 3. The aviation engine according to claim 1, wherein the heat exchanger is a surface type heat exchanger.