JP2008094189A - Fan-driven turbine system - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a technology capable of reducing the weight, the space or the cost of an entire system, by reducing necessity of providing any special device or air source for air-conditioning, separately from a device of generating propulsion force or lift for an aircraft. <P>SOLUTION: In the fan-driven turbine system using a fan device 3 for operating an air turbine 2 by extracting a part of air compressed by a compressor 11 of a gas turbine engine 1, compressed air to be introduced in the air turbine 2 is cooled by a heat exchanger 4 in advance, and also used for air-conditioning after passing through the air turbine 2. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a fan-driven turbine system that generates propulsion and lift by operating an air turbine with compressed air extracted from a gas turbine engine and driving the fan by the air turbine.

  In order to obtain propulsive force or lift of an aircraft or the like, the air turbine is rotationally driven by the energy generated when the compressed air generated by the compressor of the gas turbine engine expands, and the fan is rotated using the rotation of the air turbine. Fan driven turbine systems are known.

  As a technique for using air extracted from a gas turbine engine for air conditioning, the air extracted from a turbine is introduced into a turbo compressor provided separately from a turbine for obtaining propulsive force or lift. In addition, a technique has been proposed in which the turbine of a turbo compressor is driven and the extracted air is cooled to be used for air conditioning or refreshing for passenger cabins (for example, see Patent Document 1).

However, in the above-described technique, a thrust and lift generation system for an aircraft and an air conditioning system are provided separately, which may hinder weight, space, or cost reduction.
Japanese Patent No. 2533988

  The purpose of the present invention is to reduce the need for a special device or air source for air conditioning, apart from devices that generate propulsion and lift such as aircraft, and can reduce weight, space or cost Is to provide the technology.

  In order to achieve the above object, the present invention maximizes the use of air extracted from a gas turbine engine and cooled in a heat exchanger to be used for air conditioning, which is introduced to operate an air turbine for driving a fan. Features.

More specifically, a gas turbine engine,
An extraction passage through which pre-combustion air extracted from the gas turbine engine flows;
An air turbine that is operated by the air flowing through the extraction passage;
A fan driven by the air turbine;
A heat exchanger that is provided in the extraction passage and exchanges heat of the air passing through the extraction passage with a heat medium, and
With
The air after heat is taken away by the heat exchanger is used for air conditioning.

  According to the present invention, air extracted from a gas turbine engine and deprived of energy by an air turbine for obtaining propulsive force or lift can be used as it is for air conditioning, and a special device or air source for air conditioning can be used. There is no need to secure it separately. Therefore, the weight, space, or cost of the entire system can be reduced.

  In the present invention, the extraction passage is provided with a bypass path through which the extracted air can bypass the heat exchanger, and when the output from the fan is increased, the heat exchanger is The amount of air passing through the bypass path may be relatively increased with respect to the amount of air passing through.

  In other words, when it is desired to rapidly increase the propulsive force and lift by the fan, the air extracted from the gas turbine engine is bypassed by the heat exchanger and supplied to the air turbine at a high temperature. By doing so, the energy supplied to the air turbine can be increased and the output of the fan can be increased rapidly.

  In this case, the output of the fan can be increased rapidly by increasing the amount of air passing through the bypass path relative to the amount of air passing through the heat exchanger, but the air passing through the heat exchanger And the bypass passage may be allowed to pass through substantially the entire amount of air passing through the extraction passage.

  In the present invention, the heat exchanger may exchange heat of the air with an air flow generated by driving the fan. That is, the air may be cooled by dissipating heat of the air passing through the heat exchanger into an air flow generated by driving the fan. If it does so, the apparatus for flowing the heat carrier which should exchange the heat of the air extracted from the said gas turbine engine will become unnecessary. Specifically, a fan, a motor, a pump, or the like that supplies the heat medium to the heat exchanger can be omitted.

  In this case, the heat exchanger may use the wall surface of the duct on the downstream side of the fan as a heat transfer plate that dissipates the heat of the air. If it does so, it will become unnecessary to provide a heat exchanger plate newly in a heat exchanger, and the weight, space, or cost as the whole system can further be reduced.

  The means for solving the problems in the present invention can be used in combination as much as possible.

  In the present invention, it is possible to reduce the necessity of providing a special device or air source for air conditioning separately from a device that generates propulsive force or lift force such as an aircraft, and to reduce weight, space, or cost. .

  The best mode for carrying out the present invention will be exemplarily described in detail below with reference to the drawings.

  FIG. 1 shows a schematic configuration of the entire system including a gas turbine engine 1 and an air turbine 2 in the present embodiment. A gas turbine engine (hereinafter, simply referred to as “engine”) 1 in this embodiment includes a compressor 11, a combustor 12, and a turbine 13. Then, the air (intake air) drawn into the compressor 11 is compressed by the compressor 11, and mixed with the fuel supplied by a fuel injection device (not shown) and burned in the combustor 12, and the combustion gas is compressed by the compressor 11. And the turbine 13 directly connected to the rotary shaft 14 is driven and then discharged to the outside of the engine.

In addition, an extraction flow path 15 is connected to the compressor 11, and a part of the compressed air generated in the compressor 11 is discharged to the extraction flow path 15. Then, in the extraction flow path 15, the heat of the compressed air passing through the extraction flow path 15 is dissipated to the outside air (in other words, heat is exchanged with the air as the heat medium), and the temperature of the compressed air is lowered. A heat exchanger 4 is provided.

  Further, an air turbine 2 that is operated by compressed air passing through the extraction passage 15 is provided downstream of the heat exchanger 4 in the extraction passage 15. The air turbine 2 is actuated to drive the fan device 3 to generate propulsive force or lift.

  FIG. 2 shows a schematic configuration in the vicinity of the air turbine 2 and the fan device 3. The air turbine 2 is rotationally driven by the energy generated when the compressed air flowing in from the extraction flow passage 15 expands. The rotational motion is transmitted to the fan device 3 after being decelerated by the speed reducer 20. Then, the fan device 3 is driven to generate an air flow, thereby generating a propulsive force or lift of the airframe on which the present system is mounted.

  Here, the description returns to FIG. In FIG. 1, the temperature of the compressed air compressed by the compressor 11 of the gas turbine engine 1 rises to a high temperature of about 300 ° C., for example.

  The heat of the compressed air is taken away by the outside air in the heat exchanger 4. Accordingly, the temperature of the compressed air after passing through the heat exchanger 4 is reduced to, for example, about 150 ° C., and when the air turbine 2 is rotated, it is expanded and deprived of energy, and is discharged from the air turbine 2. Is, for example, cool air of about 5 ° C.

  In this embodiment, the cool air after rotating the air turbine 2 is used for air conditioning. For example, when this system is used in an aircraft, this air conditioning may be used for cooling a passenger seat, or may be used for cooling a luggage compartment or instruments.

  Thus, in this embodiment, since the air after driving the air turbine 2 for obtaining propulsive force or lift is used as it is for air conditioning, it is not necessary to separately provide a system for air conditioning, and the weight of the entire system , Space or cost can be reduced.

  Next, a second embodiment of the present invention will be described. In the present embodiment, an example will be described in which a bypass flow path 16 is provided for allowing the compressed air passing through the extraction flow path 15 to bypass the heat exchanger 4.

  In FIG. 3, the schematic of the whole system containing the gas turbine engine 1 and the air turbine 2 in a present Example is shown. The difference between the system according to the present embodiment and that shown in Embodiment 1 is that the extraction flow path 15 communicates the upstream side and the downstream side of the heat exchanger 4 in the extraction flow path 15, and the extraction flow path 15. The bypass flow path 16 which bypasses the heat exchanger 4 with the compressed air which passes is provided. In this embodiment, the extraction flow path 15 bypassed by the bypass flow path 16 and the extraction flow path valve 5 for controlling the amount of compressed air passing through each flow path and the bypass flow path 16 are provided. A bypass passage valve 6 is provided.

  When the propulsive force or lift force by the fan device 3 is rapidly increased, the extraction flow path valve 5 is operated to the valve closing side and the bypass flow path valve 6 is operated to the valve opening side. Thereby, the temperature of the compressed air introduced into the air turbine 2 can be made higher, and the energy supplied to the air turbine 2 can be increased rapidly.

As described above, according to the present embodiment, the amount of compressed air passing through the heat exchanger 4 and compressed air passing through the bypass flow path 16 is adjusted according to the request for propulsion or lift by the fan device 3. Therefore, it is possible to respond quickly to changes in propulsive force or lift required for the fan device 3.

  Next, a third embodiment of the present invention will be described. In the present embodiment, an example will be described in which air that is exhausted from the fan device 3 to generate propulsive force or lift is used as a heat medium that removes the heat of compressed air in the heat exchanger 4.

  FIG. 4 shows a schematic configuration of the entire system including the gas turbine engine 1 and the air turbine 2 in the present embodiment. In the present embodiment, the heat exchanger 4 is disposed downstream of the fan device 3, and the heat of the compressed air passing through the extraction channel 15 is taken away by the air flow discharged from the fan device 3.

  If it does so, the air as a heat medium can be more reliably supplied to the heat exchanger 4, and the temperature of the compressed air which distribute | circulates the extraction flow path 15 can be reduced more efficiently. Further, according to the present embodiment, it is not necessary to newly prepare a device for supplying air as a heat medium to the heat exchanger 4, which is more advantageous in terms of weight, space, and cost.

  At this time, it is desirable that the bypass flow path 16 is not disposed downstream of the fan device 3. By doing so, the temperature of the compressed air passing through the bypass channel 16 can be maintained at a higher temperature. As a result, the energy supplied to the air turbine 2 can be increased more efficiently when the propulsive force or lift by the fan device 3 is rapidly increased.

  FIG. 5 shows an example of a specific arrangement of the heat exchanger 4 in the present embodiment. FIG. 5A shows an example in which the heat transfer plate 40 of the heat exchanger 4 is directly provided in the duct 31 on the downstream side of the fan 30 in the fan device 3. In this case, on the surface of the duct 31 as the heat transfer plate 40, the extraction passage 41 is provided meandering so that the contact area of the compressed air with the air flow as the heat medium increases. In this example, the heat transfer plate 40 provided with the extraction passage 41 may be separately formed and attached to the surface of the duct 31.

  Next, as shown in FIG. 5B, heat is exchanged with the air flow discharged from the fan 30 by passing the compressed air through the inside of the stationary blade 32 disposed on the downstream side of the fan 30. It is an example. In the figure, an example is shown in which the interior of the stationary blade 32 is divided into an upstream portion and a downstream portion, and compressed air is introduced from the upstream portion and discharged from the downstream portion.

  FIG. 5C shows an example in which fins 42 for heat exchange of compressed air are provided in the duct 31 on the downstream side of the fan 30. In this example, the compressed air passes through the fins 42 in a meandering manner and radiates heat to the air flow discharged from the fan 30 during that time.

It is a figure which shows schematic structure of the whole system containing the gas turbine engine and air turbine in Example 1 of this invention. It is a figure which shows schematic structure of the air turbine and fan apparatus vicinity in Example 1 of this invention. It is a figure which shows schematic structure of the whole system containing the gas turbine engine and air turbine in Example 2 of this invention. It is a figure which shows schematic structure of the whole system containing the gas turbine engine and air turbine in Example 3 of this invention. It is a figure which shows the example of arrangement | positioning of the heat exchanger in Example 3 of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Gas turbine engine 2 ... Air turbine 3 ... Fan apparatus 4 ... Heat exchanger 5 ... Extraction flow path valve 6 ... Bypass flow path valve 11 ... Compressor 12 .... -Combustor 13 ... Turbine 14 ... Rotating shaft 15 ... Extraction passage 16 ... Bypass passage 30 ... Fan 31 ... Duct 32 ... Stator blade 40 ... Heat transfer Plate 41 ... Extraction passage 42 ... Fin

Claims (4)

A gas turbine engine,
An extraction passage through which pre-combustion air extracted from the gas turbine engine flows;
An air turbine that is operated by the air flowing through the extraction passage;
A fan driven by the air turbine;
A heat exchanger that is provided in the extraction passage and exchanges heat of the air passing through the extraction passage with a heat medium, and
With
A fan-driven turbine system, wherein the air after heat is taken away by the heat exchanger is used for air conditioning. The extraction passage is provided with a bypass passage that bypasses the heat exchanger,
The amount of the air passing through the bypass path is increased relative to the amount of the air passing through the heat exchanger when the output from the fan is increased. Fan driven turbine system.   The fan-driven turbine system according to claim 1 or 2, wherein the heat exchanger exchanges heat of the air with an air flow generated by driving the fan. A duct is provided around the fan,
The wall surface of the duct on the downstream side of the fan is used as a heat transfer plate that dissipates heat of the air into an air flow generated by driving the fan in the heat exchanger. Fan drive turbine system.

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