JPH05193579A - Turboshaft engine - Google Patents

Abstract

PURPOSE:To improve the safety for the engine trouble, reduce the cost, reduce the weight, and save the space, even in the state where only one engine is provided. CONSTITUTION:A turboshaft engine for helicopter is constituted of a series double turboshaft engine 1 equipped with a main engine 12 and an auxiliary engine 13 which are arranged in series on an engine output shaft 11. The output shaft 124a of the power turbine 124 of the main engine 12 and the engine output shaft 11 and the output shaft 124a of the power turbine 134 of the auxiliary engine 13 are joined by unidirectional clutches 14 and 15, respectively. The series double turboshaft engine 1 is installed on the helicopter, and in the normal fleight, the necessary output is supplied by the output sum of the main engine 12 and the auxiliary engine 13, while if the main engine 12 fails, the necessary output is supplied by the auxiliary engine 13.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION This invention relates to turboshaft engines for helicopters.

[0002]

2. Description of the Related Art Generally, helicopter turbo shafts
Engines include single turboshaft engines and double turboshaft engines.

A single turboshaft engine helicopter is equipped with one turboshaft engine 21 as a power source, as shown in FIG. This turboshaft engine 21 has one compressor 21
1, a combustor 212, a gas generator turbine 213, and a power turbine 214. The output of the single turboshaft engine realized by the single turboshaft engine 21 is input to the transmission 23 of the helicopter via the engine output shaft 22.

On the other hand, as shown in FIG. 3, the double turboshaft engine helicopter is equipped with two turboshaft engines 31 having the same structure as a power source. The configuration of each turboshaft engine 31 is the same as that of the turboshaft engine 21 installed in the helicopter of the single turboshaft engine of FIG.
One compressor 311 and one combustor 31 respectively
It is composed of two, one gas generation turbine 313 and one power turbine 314. The output of the double turboshaft engine realized by the two turboshaft engines 31 having the same structure is input to the transmission 33 of the helicopter via the two engine output shafts 32.

In the double turboshaft engine helicopter shown in FIG. 3, when one of the two turboshaft engines 31 fails, the other engine (3
It is possible to fly by the output of 1).

[0006]

The above-mentioned conventional helicopter for a turboshaft engine has the following problems. (1) With a single turboshaft engine helicopter, flight other than autorotation is not possible when the engine fails, and there is a great risk.

(2) With a double turboshaft engine helicopter, it is possible to fly even when one of the engines fails, and although there is an advantage that redundancy against the risk of engine failure is increased, two turboshafts are used. -Since the engine is required, there are problems such as high cost, large space, and weight increase regarding the engine equipment, and since the two output shafts are input to the transmission, the structure of the transmission becomes complicated, and There was a problem of high cost and weight increase.

The present invention has been made in order to solve the above-mentioned problems, and its object is to have the same structure as that of a conventional turboshaft engine equipped with two engines, although it has the form of one engine equipped with safety. It is an object of the present invention to provide a turboshaft engine for a helicopter which can be reduced in cost, reduced in weight, and space-saving by being configured to a high degree and having a single engine.

[0009]

SUMMARY OF THE INVENTION The present invention comprises a turboshaft engine for a helicopter comprising a series dual turboshaft engine having a main engine and an auxiliary engine arranged in series on an engine output shaft. However, it is characterized in that the required output is obtained by the sum of the outputs of the main engine and the auxiliary engine during normal flight, and the required output is obtained by the auxiliary engine when the main engine fails.

[0010]

[Function] By equipping the helicopter with one inline dual turboshaft engine having the above-mentioned configuration, the output required to continue flight and make an emergency landing at the time of main engine failure is at the maximum output of the auxiliary engine. Therefore, it is possible to improve the safety against engine failure even though the engine is equipped with one engine. Also,
By equipping only one engine, the cost, weight, and space can be reduced compared to the conventional double turboshaft engine which takes the form of two engines.

[0011]

1 is a diagram showing the structure of an in-line double turboshaft engine according to an embodiment of the present invention and the overall construction of a helicopter equipped with the same engine.

In FIG. 1, reference numeral 1 is an in-line double turboshaft engine, and one helicopter is installed as shown in FIG. This series double turbo shaft
The engine 1 is coupled to the transmission 2 via an engine output shaft 11 described later.

The series double turboshaft engine 1 is
As shown in FIG. 1 (b), it has a single engine output shaft 11, and is composed of a main engine 12 and an auxiliary engine 13 arranged in series on the engine output shaft 11.

The main engine 12 includes a compressor (main engine compressor) 121, a combustor (main engine combustor) 122, a gas generator / turbine (main engine gas generator / turbine) 123, and a power turbine (main engine power turbine). Having 124.

The auxiliary engine 13 is the main engine 12
As well as the compressor (auxiliary engine compressor)
131, Combustor (Auxiliary Engine Combustor) 132, Gas Gene Turbine (Auxiliary Engine Gas Gene Turbine)
133, and a power turbine (auxiliary engine power
Turbine). This auxiliary engine 13 is relatively smaller than the main engine 12, but when the main engine 12 fails, it can generate the maximum output (MAX output) necessary for continuing flight and urgently landing. It looks like this.

Power turbine 124 of main engine 12
The output shaft 124a and the engine output shaft 11 are connected by the one-way clutch 14 interposed therebetween, and the operation of the auxiliary engine 13 is not disturbed when the main engine 12 fails.

Similarly, the output shaft 134a of the power turbine 134 of the auxiliary engine 13 and the engine output shaft 11 are connected by a one-way clutch 15 interposed therebetween, and when the auxiliary engine 13 fails, It has a structure that does not hinder the operation.

In the configuration of FIG. 1, the in-line double turboshaft engine 1 equipped in the helicopter is
Although it has two engines, a main engine 12 and an auxiliary engine 13, it has one engine similar to the conventional single turboshaft engine because it has a structure in which it is connected in series on the engine output shaft 11. It will be in the form of.

Now, as shown in FIG. 1 (a), the in-line double turboshaft engine 1 of the structure shown in FIG. 1 (b) mounted on the helicopter has
The output required for flight is obtained by the sum of the outputs of both the main engine 12 and the auxiliary engine 13 that are connected in series on the engine output shaft 11, and is transmitted to the transmission 2 via the engine output shaft 11.

On the other hand, when, for example, the main engine 12 in the in-line double turboshaft engine 1 fails, the output required to continue flight and make an emergency landing is
Obtained at the maximum output of the auxiliary engine 13. Here, the one-way clutch 14 is interposed between the output shaft 124 a of the power turbine 124 of the main engine 12 and the engine output shaft 11. Therefore, the failure of the main engine 12 does not hinder the operation of the auxiliary engine 13.

If the auxiliary engine 13 in the in-line double turboshaft engine 1 fails, the flight is continued with the output of the main engine 12. A one-way clutch 15 is interposed between the output shaft 134a of the power turbine 134 of the auxiliary engine 13 and the engine output shaft 11. Therefore, the failure of the auxiliary engine 13 does not hinder the operation of the main engine 12.

[0022]

As described above in detail, according to the present invention, a turboshaft engine for a helicopter is provided with a main engine and an auxiliary engine, which are arranged in series on an engine output shaft, in a series double turboshaft.・ Composed of an engine,
This engine was installed in one helicopter to obtain the required output by the sum of the outputs of the main engine and the auxiliary engine during normal flight, and the output required for emergency landing by the auxiliary engine when the main engine failed. Although it is a basic equipment form, it is possible to improve safety against engine failure.

Also, with the equipment of only one engine, 2
Cost, weight, and space can be reduced compared to the conventional double turboshaft engine that takes the basic engine equipment form.

[Brief description of drawings]

FIG. 1 is a diagram showing a structure of an in-line double turboshaft engine according to an embodiment of the present invention and an overall configuration of a helicopter equipped with the engine.

FIG. 2 is a diagram showing the entire structure of a conventional turboshaft engine and a helicopter equipped with a single turboshaft engine configured by using the same engine.

FIG. 3 is a diagram showing the entire structure of a conventional turboshaft engine and a helicopter equipped with a double turboshaft engine configured by using two of the same engines.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... In-line dual turbo shaft engine, 2 ... Transmission, 11 ... Engine output shaft, 12 ... Main engine, 13 ... Auxiliary engine, 14, 15 ... One-way clutch, 121, 131 ... Compressor, 122, 132 ...
Combustor, 123, 133 ... Gas generator / turbine, 12
4,134 ... Power turbine.

Claims (1)

[Claims] 1. A helicopter in-line dual turboshaft engine, comprising a main engine and an auxiliary engine connected in series on an engine output shaft, wherein the outputs of the main engine and the auxiliary engine are output during normal flight. A series double turboshaft engine for helicopters, characterized in that the required output is supplied by the sum, and the required output is supplied by the auxiliary engine when the main engine fails.