JPH0687640U - Gas turbine engine - Google Patents

Abstract

(57) [Abstract] [Purpose] It is not necessary to secure a special space for arranging the starter generator outside the engine casing, and downsizing can be achieved, and the power transmission loss between the starter generator and the high-pressure shaft is reduced. A gas turbine engine is provided. A sump chamber (20) formed between a low pressure compressor (2) and a high pressure compressor (4) is provided with a starter generator (10) having its rotor (21) outside and a stator (22). ) Are arranged inside and the rotor of the starter generator is connected to the power transmission system (26, 27).
Connected to the front end of the high pressure shaft (72) via
Lower the stator pressure. It is supported by a connecting member (28) extending from a vane support (29) of the high pressure compressor.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention mainly relates to a gas turbine engine used for aircraft.

[0002]

[Prior art]

 FIG. 3 shows an example of a conventionally used gas turbine engine. In this gas turbine engine, the inflow air taken in through the air intake 1 is first compressed by the low pressure compressor 2. Then, a part of the compressed air sent from the low-pressure compressor 2 passes through the fan air discharge duct 3 and is directly injected outside the engine as a bypass thrust.

On the other hand, the remaining compressed air sent from the low-pressure compressor 2 is further compressed to a high pressure by the high-pressure compressor 4, and then sent to the combustion chamber 5 to burn the supplied fuel. The high temperature combustion gas discharged from the combustion chamber 5 rotates the high pressure turbine 61 and the low pressure turbine 71, and is ejected from the exhaust duct 8 as a core thrust.

The low pressure compressor 2 is composed of a moving blade 2 a and a stationary blade 2 b, and the moving blade 2 a is connected to the low pressure turbine 71 via a low pressure shaft 72. The high-pressure compressor 4 is composed of a moving blade 4a and a stationary blade 4b, and the moving blade 4a is connected to the high-pressure turbine 61 via a high-pressure shaft 62.

By the way, a starter generator 10 is usually mounted on a small gas turbine engine of this type. The starter generator 10 operates as a starter when the engine starts and operates as a generator after the engine starts.

That is, the starter generator 10 is arranged adjacent to the accessory gearbox 11, and is connected to the high pressure shaft 62 via the tower shaft 12 and the bevel gear 13 connected to it.

At the time of start-up, the high-pressure shaft 62 is driven by the battery mounted onboard the machine to forcefully rotate the high-pressure shaft 62 via the tower shaft 12 and the like, and the compressed air is sent to the combustion chamber 5 to make the engine self-sustaining. Enables driving.

Once the engine is started, the starter generator 10 operates as a generator and uses the rotational energy obtained via the tower shaft 12 to charge the battery and supply the onboard electrical energy.

[0009]

[Problems to be solved by the device]

 In the conventional jet engine, since the starter generator 10 is attached to the auxiliary equipment gear box 11 and is arranged outside the engine casing 14, a special space is required to arrange the starter generator 10. There was a problem.

Further, the starter generator is connected to the high-pressure shaft via the power transmission system such as the tower shaft 12, and there is a problem that friction loss occurs in these power transmission systems.

The present invention has been made in view of the above circumstances, and it is not necessary to secure a special space for arranging the starter generator outside the engine casing, and only between the starter generator and the high pressure shaft. It is an object of the present invention to provide a gas turbine engine that can reduce power transmission loss of the engine.

[0012]

[Means for Solving the Problems]

 In order to achieve the above object, the present invention arranges a starter generator in a sump chamber formed between a low pressure compressor and a high pressure compressor, the starter generator having its rotor on the outside and the stator on the inside. Respectively, the rotor is connected to a high pressure shaft for driving the high pressure compressor via a power transmission system, and the stator is connected to the low pressure. The structure is supported by a connecting member extending from the stationary blade supporting portion of the high-pressure compressor.

[0013]

[Action]

 By arranging the starter generator in the sump chamber formed between the low-pressure compressor and the high-pressure compressor, it is possible to effectively use the sump chamber, which is the originally existing space, and thus the starter generator is provided outside the engine casing. There is no need to reserve a special space for placing the. Also, since the rotor of the starter generator can be placed close to the rotor blades of the high-pressure compressor, the conventionally used members such as the tower shaft are no longer required, which simplifies the power transmission system and therefore the power transmission. Friction loss lost in the system can also be reduced.

[0014]

【Example】

 The gas turbine engine of the present invention will be described below with reference to FIGS. The same components as those described in the conventional example are designated by the same reference numerals to simplify the description.

In this embodiment, the starter generator 10 is arranged in a sump chamber 20 formed between the low pressure compressor 2 and the high pressure compressor 4. The starter generator 10 comprises a rotor 21 and a stator 22, where the rotor 21 is arranged on the outside and the stator 22 is arranged on the inside.

As shown in FIG. 2, each of the rotor 21 and the stator 22 is provided with a component E such as a magnet and a coil as well known, and a cord 23 electrically connected to the coil from the stator 22. Is extended.

Bearings 25, 25 are provided at the front and rear ends of the rotor 21 and the stator 22 (here, the front and rear are defined based on the air flow, and the left side in FIG. 1 is the front and the right side is the rear). It is mounted to allow their relative rotation.

A bevel gear 26 is formed at a rear end inclined so as to narrow inward of the rotor 21, and meshes with a bevel gear 27 extending from a high pressure shaft 62. On the other hand, a connecting member 28 that spreads obliquely forward is integrally attached to the front end of the stator 22, and the front end of the connecting member 28 is the low pressure. It is connected to a support portion 29 that supports the stationary blades 2b and 4b of the high-pressure compressor. Further, a bearing 30 is interposed between the stator 22 and the low pressure shaft 72.

Therefore, according to the gas turbine engine having the above-described configuration, by arranging the starter generator 10 in the sump chamber 20 formed between the low-pressure compressor 2 and the high-pressure compressor 4, the space that originally exists. It is possible to effectively utilize the sump chamber 20, which is not necessary to secure a special space for arranging the starter generator 10 outside the engine casing 14 as shown in the related art, and to downsize the device. Can be achieved.

Further, compared to the conventional one, the rotor 21 of the starter generator 10 can be arranged closer to the high-pressure shaft 62, so that a member such as a tower shaft is unnecessary, and the power transmission system is simplified. Can be achieved. Therefore, the friction loss lost in the power transmission system can be reduced and the output can be increased.

Further, the stator 22 is supported by the connecting member 28 extending from the support portion 29 that supports the stationary blades 2 b and 4 b of the compressor, and the bearing 30 is provided between the stator 22 and the low pressure shaft 72. As a result, the low pressure shaft 72 can be finally supported by the support portion 29 via the stator 22. That is, by using the stator 22, the supporting point of the low pressure shaft 72 can be secured also here, and the strength of the entire engine is not impaired by incorporating the starter generator.

The structure of the gas turbine engine of the present invention is not limited to the above-mentioned embodiment, and the specific constituent elements such as the shape, material, size and construction procedure of each member may be appropriately changed during the execution. It can be changed.

For example, in the above-described embodiment, the rotation of the rotor 21 is transmitted to the high-pressure turbine shaft 62 via the bevel gears 26 and 27, but the transmission system is not limited to this and a spline or chain or the like may be used. It may be one.

[0024]

[Effect of device]

 The present invention has the following effects.

By arranging the starter generator in the sump chamber formed between the low pressure compressor and the high pressure compressor, it is possible to effectively use the originally existing space, that is, the engine casing. Since it is not necessary to secure a special space for arranging the starter generator outside the engine, the overall size of the engine can be reduced.

Since the rotor of the starter generator can be arranged close to the high-pressure shaft, members such as the power shaft are unnecessary, the power transmission system can be simplified, and the friction loss lost in the power transmission system can be reduced.

[Brief description of drawings]

FIG. 1 is an overall schematic cross-sectional view of a gas turbine engine according to the present invention.

FIG. 2 is a cross-sectional view of a main part of the gas turbine engine.

FIG. 3 is an overall schematic sectional view showing an example of a conventional gas turbine engine.

[Explanation of symbols]

 2 low-pressure compressor 2a moving blade 2b stationary blade 4 high-pressure compressor 4a moving blade 4b stationary blade 6 high-pressure turbine 62 high-pressure shaft 7 low-pressure turbine 72 low-pressure shaft 10 starter generator 20 sump chamber 21 rotor 22 stator 26 power transmission system (bevel gear) ) 27 power transmission system (bevel gear) 28 connecting member 29 support section

Claims (1)

[Scope of utility model registration request] 1. A starter generator is disposed in a sump chamber formed between a low pressure compressor and a high pressure compressor, and the starter generator has its rotor positioned outside and the stator positioned inside. , The rotor is connected to a high pressure shaft for driving the high pressure compressor via a power transmission system, and the stator is connected to the low pressure. A gas turbine engine, which is supported by a connecting member extending from a stationary blade supporting portion of a high-pressure compressor.