JP4165279B2 - Telemeter cooling device in gas turbine engine - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a telemeter cooling device in a gas turbine engine provided with a telemeter for detecting the state of a rotating system such as blade vibration in the development of the gas turbine engine for aircraft, for example. More specifically, the present invention relates to a telemeter cooling device in a gas turbine engine that can cool the telemeter even after the gas turbine engine is stopped.
[0002]
[Prior art]
Conventionally, when developing a gas turbine engine for an aircraft, for example, a telemeter or the like has been incorporated into the developed gas turbine engine for an aircraft in order to extract measurement data of a rotating system such as blade vibration outside the gas turbine engine. Yes.
[0003]
In general, telemeters are expensive and have a lower allowable temperature than other components and cannot withstand high temperatures, so telemeters incorporated in gas turbine engines are typically cooled by oil. When the telemeter is cooled with oil in this way, the oil pump is also stopped when the development gas turbine engine is stopped. Therefore, the temperature of the telemeter may increase due to residual heat of the gas turbine engine.
[0004]
[Problems to be solved by the invention]
Therefore, conventionally, it is necessary to rotate the rotor with a starter and drive the oil pump so that the telemeter can be cooled even after the rotation of the gas turbine engine is stopped. There is a problem that there are significant restrictions on various measurement systems and operation procedures.
[0005]
[Means for Solving the Problems]
The present invention has been made in view of the conventional problems as described above, and in the present invention, a telemeter for detecting the state of the rotating part is disposed at the rotating part or a position close to the rotating part in the gas turbine engine. An air outlet for ejecting cooling air to the telemeter is provided at a position close to the telemeter, and the air outlet is connected to an external air source via a connection path. Is provided with an on-off valve that opens when the gas turbine engine is stopped.
[0007]
DETAILED DESCRIPTION OF THE INVENTION
DESCRIPTION OF EMBODIMENTS Hereinafter, embodiments of the present invention will be described with reference to the drawings. In order to facilitate understanding, a general configuration of a gas turbine engine to which the present invention is applied will be described.
[0008]
Referring to FIG. 1, a jet engine is illustrated as a gas turbine engine 1 according to the present embodiment. The gas turbine engine 1 includes a cylindrical cowl 3, and a cylindrical casing 7 is disposed in the cowl 3 via a plurality of stays 5. An annular bypass 9 is formed between the inner peripheral surface of the cowl 3 and the outer peripheral surface of the casing 7.
[0009]
In the casing 7, a core engine 17 including a high-pressure compressor 11, a combustor 13, and a high-pressure turbine 15 is provided. The high-pressure compressor 11 and the high-pressure turbine 15 are configured to rotate integrally with a hollow high-pressure turbine shaft 19, and the high-pressure turbine shaft 19 can be freely rotated by a fixed portion 23 via a rotary bearing 21. It is supported.
[0010]
A fan rotor blade 27 and a low-pressure compressor 29 for taking in air from an air intake port 25 are provided on the front side of the core engine 17, and a low-pressure turbine 31 is provided on the rear side of the high-pressure turbine 15. The fan rotor blade 27 and the low-pressure compressor 29 are configured to rotate integrally with the low-pressure turbine 31 through a low-pressure turbine shaft 33 that penetrates the high-pressure turbine shaft 19. The low-pressure turbine shaft 33 is rotatably supported by the fixed portion 23 via a plurality of bearings 35.
[0011]
In the above configuration, when the gas turbine engine 1 is started, the fan rotor blade 27 rotates and air is taken in from the air intake port 25. The air taken in by the rotation of the fan rotor blade 27 is divided into a bypass flow 35A flowing into the bypass passage 9 and a core flow 35B flowing into the core engine 17 side.
[0012]
The core stream 35B is gradually compressed into a high-temperature and high-pressure gas by the low-pressure compressor 29 and the high-pressure compressor 11, and this high-temperature and high-pressure gas is injected into the combustor 13 and fuel is injected into the combustor 13 and ignited. Then, high-temperature and high-pressure combustion gas is injected backward. The high-pressure turbine 15 and the low-pressure turbine 31 are rotated by the backward injection of the high-temperature and high-pressure combustion gas.
[0013]
The rotation of the high pressure turbine 15 is transmitted to the high pressure compressor 11 via the high pressure turbine shaft 19, and the rotation of the low pressure turbine 31 is transmitted to the fan rotor blade 27 and the low pressure compressor 29 via the low pressure turbine shaft 33.
[0014]
In the gas turbine engine 1 having the above-described configuration, a telemeter 37 (see FIG. 2) is incorporated in the development engine in order to detect the rotational state of a rotating system such as blade vibration.
[0015]
FIG. 2 is an enlarged view of portion A in FIG. 1, and in this embodiment, a case where a telemeter 37 is provided on the high-pressure turbine shaft 19 is illustrated. In the present embodiment, the telemeter 37 is attached to the high-pressure turbine shaft 19 between an annular cup-shaped seal ring 39 attached to the high-pressure turbine shaft 19 and the rotary bearing 21.
[0016]
An annular seal support member 41 surrounding the sealing 39 is attached to the fixed portion 23, and this seal support member 41 cooperates with a labyrinth packing (not shown) provided on the high-pressure turbine shaft 19. A labyrinth seal member 43 constituting a labyrinth seal is provided, and an annular seal member 45 in contact with the outer peripheral surface of the seal ring 39 is provided on the inner peripheral surface of the seal support member 41.
[0017]
Further, an annular receiver support member 47 is attached to the fixed part 23, and a receiver 49 for receiving measurement data from the telemeter 37 is close to the telemeter 37 on the receiver support member 47. It is provided.
[0018]
Further, the fixing portion 23 is provided with an oil mist injection port (not shown) for injecting cooling oil mist to the telemeter 37, and an air outlet 51 for injecting cooling air to the telemeter 37. A nozzle member 53 is provided. The air outlet 51 is connected to an external air source (not shown) through a flow path formed in the fixed portion 23 and a pipe 57 disposed in the stay 5. An on-off valve 59 (see FIG. 1) is arranged.
[0019]
The air source is, for example, an air pipe provided in a factory. The on-off valve 59 is normally closed, and is opened under the control of a control device (not shown) when the rotation of the development gas turbine engine 1 is stopped.
[0020]
In the above-described configuration, when the gas turbine engine 1 is driven, for example, the rotation state of the high-pressure turbine shaft 19 is detected by the telemeter 37, and the measurement data is received by the receiver 49, and a lead wire (illustrated) arranged in the stay 5 portion. It is taken out via (omitted). Then, the oil supply pump is driven to rotate in conjunction with the rotation of the gas turbine engine 1, and oil mist is injected from the oil mist injection port toward the telemeter 37 to cool the telemeter 37.
[0021]
When the gas turbine engine 1 is stopped, the open / close valve 59 is opened under the control of the control device, and cooling air is ejected from the air injection port 51 toward the telemeter 37. The cooling air ejected from the air ejection port 51 passes through a hole 47H provided in the receiving portion support member 47 and is directly injected into the telemeter 37, whereby the telemeter 37 is cooled.
[0022]
As described above, cooling air is injected into the telemeter 37 to cool the telemeter 37, and a predetermined time has elapsed since the gas turbine engine 1 stopped, or the temperature of the gas turbine engine 1 has decreased below a predetermined temperature. When this is detected, the on-off valve 59 is closed to stop the cooling air jet.
[0023]
As already understood, in the present embodiment, after the driving of the gas turbine engine 1 is stopped, cooling air is introduced into the gas turbine engine 1 from an external air source and incorporated into the gas turbine engine 1. Since the telemeter cools the telemeter by injecting cooling air into the telemeter, it is not necessary to rotate the oil pump with a starter for refueling after the gas turbine engine 1 stops rotating, eliminating the conventional problems described above. It is possible.
[0024]
Note that the present invention is not limited to the above-described embodiment, and can be implemented in other forms by making appropriate modifications. That is, in the above description, it has been described that the injection port for injecting oil mist to the telemeter 37 and the air injection port 51 for injecting cooling air are provided separately. However, the injection for injecting the air injection port 51 and the oil mist is described. It is also possible to have a common configuration for the mouth.
[0025]
Further, instead of the configuration in which the oil mist is injected to the telemeter 37 when the gas turbine engine 1 is rotated, it is also possible to have a configuration in which cooling air is always ejected from the air ejection port 51 to cool the telemeter 37.
[0026]
【The invention's effect】
As will be understood from the above description, according to the present invention, after the rotation of the gas turbine engine is stopped, the cooling air is introduced from the external air source, injected into the telemeter, and cooled. Therefore, it is not necessary to rotate the oil pump by the starter after the rotation stops, so that the conventional problems as described above can be solved.
[Brief description of the drawings]
FIG. 1 is an explanatory diagram schematically showing an overall configuration of a gas turbine engine to which the present invention is applied.
FIG. 2 is an enlarged explanatory view of a portion A in FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Gas turbine engine 5 ... Stay 11 ... High pressure compressor 13 ... Combustor 15 ... High pressure turbine 17 ... Core engine 19 ... High pressure turbine shaft 23 ... Fixed part 29 ... Low pressure compressor 31 ... Low pressure turbine 33 ... Low pressure turbine shaft 37 ... Telemeter 47 ... receiving portion support member 49 ... receiver 51 ... air outlet 53 ... nozzle member 55 ... flow path 57 ... piping 59 ... on-off valve

Claims (1)

A telemeter for detecting the state of the rotating part is arranged at a position close to the rotating part or the rotating part in the gas turbine engine, and for injecting cooling air to the telemeter at a position close to the telemeter. An air spout is provided , and the air spout is connected to an external air source through a connection path, and an opening / closing valve that is opened when the gas turbine engine is stopped is disposed in the connection path. A telemeter cooling device in a gas turbine engine.

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