JPH07190373A - Catalytic combustor starting method for gas-turbine engine - Google Patents

Abstract

PURPOSE:To prevent unburnt gas from being exhausted by quickly shifting a gas-turbine engine to the steady state of combustion after starting thereof. CONSTITUTION:A compressed air-preheating means 17 and catalytic support- preheating means 26, 27 are energized for a fixed time, and the temperature thereof is allowed to rise, following which a starter 32 is started in an open state of a bypass valve 14. When the starter 32 begins to be rotated at a fixed value, the bypass valve 14 is closed, following which air temperature at the inlet of a catalytic combustion part 23 becomes at a temperature or higher, at which a catalyst is activated, and the temperature of catalytic supports 24, 25 becomes at the air temperature at the inlet or higher and becomes much the same as the distribution of temperature in a steady state of operation. At this time, the electric current applied to both of the preheating means 17, 26, 27 is turned off, fuel begins to be sprayed by a fuel-spraying nozzle 29, and combustion by catalytic reaction is generated at the catalytic combustion part 23.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel mixing portion in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed with a mixture of the compressed air and the fuel. The present invention relates to a method for starting a catalytic combustor for a gas turbine engine, the method including a catalytic combustion unit that burns the fuel in a fuel cell.

[0002]

2. Description of the Related Art In a gas turbine engine as well as in a reciprocating engine, harmful nitrogen oxides (hereinafter referred to as NOx) are generated in the exhaust gas, and the NOx emission amount increases as the combustion temperature of the air-fuel mixture increases. In the conventional combustor for gas turbine engine, it is difficult to reduce the emission amount of NOx because the combustion temperature of the air-fuel mixture reaches an extremely high temperature (for example, 2000 ° C.). Therefore, a combustor for a gas turbine engine has been proposed as a so-called catalytic combustion method in which a gas mixture is brought into contact with a catalyst provided inside the combustor and burned. According to this catalytic combustion method, since the combustion of the air-fuel mixture in the combustor is performed at a relatively low temperature, it is possible to significantly reduce NOx in the exhaust gas.

In the gas turbine engine equipped with the above-mentioned catalytic combustor, the temperature of the catalyst carrier is maintained at the catalyst activation temperature or higher once the steady combustion operation state is entered, but the preheating means is used at the time of starting. Therefore, it is necessary to preheat the temperature of the catalyst carrier above the catalyst activation temperature. Therefore, it is proposed to preheat the compressed air supplied to the catalytic combustor or the catalyst carrier of the catalytic combustor to the catalyst activation temperature or higher by using an electric preheating means at the time of starting the gas turbine engine (for example, JP-A-60-36813,
(See JP-A-59-180220).

[0004]

However, it is difficult for the above-mentioned conventional catalytic combustor for gas turbine engine to obtain a steady combustion state immediately after the start, and unburned gas is generated before the transition to the steady combustion state. There was a problem of being discharged.

The present invention has been made in view of the above-mentioned circumstances, and by appropriately controlling the preheating means at the time of starting the gas turbine engine, the steady combustion state can be rapidly changed to suppress the discharge of unburned gas. At the same time, it is an object of the present invention to shorten the time required for the preheating at the time of starting, to enable quick starting, and to prevent the catalyst carrier from being damaged by preheating.

[0006]

In order to achieve the above object, the invention described in claim 1 is a fuel mixture in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed. Part, a catalytic combustion part for combusting a mixture of the compressed air and the fuel by a catalytic reaction, a compressed air preheating means for electrically preheating the compressed air, and a catalyst carrier of the catalytic combustion part electrically. In a method for starting a catalytic combustor for a gas turbine engine, which comprises a catalyst carrier preheating means capable of preheating, the inlet air temperature of the catalytic combustion part is equal to or higher than the catalyst activation temperature before the combustion by the fuel supply from the fuel injection nozzle is started. In addition to preheating, the temperature of the catalyst carrier or the outlet air temperature of the catalyst combustion section is preheated to the inlet air temperature or higher.

In addition to the structure of claim 1, the invention described in claim 2 makes the temperature distribution of the catalyst carrier along the flow direction of the air-fuel mixture such that the downstream temperature is higher than the upstream temperature. It is characterized by setting.

According to a third aspect of the invention, in addition to the structure of the second aspect, the catalyst carriers are arranged in a plurality of stages along the flow direction of the air-fuel mixture, and the temperature of the downstream catalyst carrier is set to the upstream side. It is characterized in that the temperature is set to be higher than the temperature of the side catalyst carrier.

In addition to the structure of claim 2, the invention according to claim 4 controls the temperature distribution of the catalyst carrier by the amount of electricity supplied to the catalyst carrier preheating means and / or the amount of compressed air supplied to the catalyst carrier. It is characterized by doing.

The invention described in claim 5 is characterized in that, in addition to the constitution of claim 1, the catalyst carrier preheating means is arranged immediately before the inlet of the catalyst carrier.

According to a sixth aspect of the invention, there is provided a fuel mixing section in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed, and a mixture composed of the compressed air and the fuel. In a method for starting a catalytic combustor for a gas turbine engine, comprising: a catalytic combustion part for combusting a gas by a catalytic reaction; and a preheating means capable of electrically preheating the compressed air and / or the catalyst carrier of the catalytic combustion part,
It is characterized in that the preheating means is energized for a predetermined time before the start of the start-up by the starter.

In addition to the structure of claim 6, the invention described in claim 7 is characterized in that the compressed air supplied to the preheating means is bypassed and / or extracted for a predetermined time after the start of the starter. And

Further, the invention described in claim 8 is a fuel mixing section in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed, and a mixture composed of the compressed air and the fuel. In a method for starting a catalyst combustor for a gas turbine engine, comprising: a catalyst combustion part for combusting a catalyst by a catalytic reaction; and a catalyst carrier preheating means capable of electrically preheating the catalyst carrier of the catalyst combustion part. When the temperature of the catalyst carrier or the temperature of the catalyst outlet air reaches a predetermined temperature, fuel supply from the fuel injection nozzle is started, and at the same time as or after a predetermined time, power supply to the catalyst carrier preheating means is stopped.

Further, the invention described in claim 9 is that a fuel mixing portion in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed, and a mixture gas composed of the compressed air and the fuel. In a catalytic combustor for a gas turbine engine, comprising:
It is characterized in that the temperature is kept below ℃.

In addition to the structure of claim 9, the invention described in claim 10 controls the ratio of the amount of air passing through the catalytic combustion portion and the amount of air bypassing the catalytic combustion portion to control the inlet of the turbine. The air temperature is kept at 400 ° C. or lower.

According to the invention described in claim 11, a fuel mixing portion in which compressed air supplied from a compressor and fuel supplied from a fuel injection nozzle are mixed, and a mixture composed of the compressed air and the fuel are mixed. In a method for starting a catalytic combustor for a gas turbine engine, which comprises a catalytic combustion unit for combusting a gas by a catalytic reaction, the starter load is controlled so that the engine speed before and after the start of fuel supply does not suddenly change. .

According to a twelfth aspect of the present invention, a fuel mixing section in which the compressed air supplied from the compressor and the fuel supplied from the fuel injection nozzle are mixed, and a mixture composed of the compressed air and the fuel. In a method of starting a catalytic combustor for a gas turbine engine, which comprises a catalytic combustion unit for combusting a catalyst by a catalytic reaction, it is possible to control the amount of catalyst bypass air so that the amount of air passing through the catalyst does not change rapidly before and after the start of fuel supply. Characterize.

According to a thirteenth aspect of the present invention, there is provided a fuel mixing section in which the compressed air supplied from the compressor and the fuel supplied from the fuel injection nozzle are mixed, and a mixture composed of the compressed air and the fuel. In a method for starting a catalytic combustor for a gas turbine engine, comprising: a catalytic combustion part for combusting a gas by a catalytic reaction; and a gas phase combustion part for combusting an air-fuel mixture in a gas phase reaction downstream of the catalytic combustion part. It is characterized by having a means for preheating the air.

According to a fourteenth aspect of the present invention, in addition to the configuration of the thirteenth aspect, the means for preheating the air in the gas phase combustion section electrically preheats the preheater and the catalyst carrier installed upstream of the catalyst. One of a possible catalyst heater, a preheater installed immediately after the catalyst, and a wall heater disposed downstream of the catalyst, or a combination thereof.

In addition to the structure of the thirteenth aspect of the present invention, the fuel supply is started after the air temperature of the gas phase combustion section or the wall surface temperature downstream of the catalyst is preheated to a predetermined temperature. It is characterized by doing.

[0021]

Embodiments of the present invention will be described below with reference to the drawings.

1 to 4 show a first embodiment of the present invention. FIG. 1 is a longitudinal sectional view of a gas turbine engine, FIG. 2 is an enlarged view of a main part of FIG. 1, and FIG. -3 line sectional view, FIG.
FIG. 3 is a diagram showing a temperature distribution inside a gas turbine engine.

The single-shaft gas turbine engine G has a rotary shaft 3 supported by bearings 1 and 2, and a rotary compressor 4 and a centrifugal turbine 5 are provided on the rotary shaft 3. The compressor 4 is the compressor rotor 6
The air sucked through the air cleaner 8 and the intake passage 9 is compressed into a high temperature and high pressure state and supplied to the front compressed air passage 10. A part of the heat exchanger 11 that recovers the heat of the combustion gas faces the front compressed air passage 10, and the compressed air that has been further heated after passing through the heat exchanger 11 is supplied to the rear compressed air passage 12. To be done. A bypass valve 14 connected to a solenoid 13 is attached to an intermediate portion of the rear compressed air passage 12, and an upstream position of the bypass valve 14 and a combustion gas passage 15 described later are connected by a bypass passage 16.

On the downstream side of the rear compressed air passage 12, there is provided an annular compressed air preheating means 17 which is energized to generate heat when the gas turbine engine G is started. A cylinder that constitutes the fuel mixing section 18 is provided downstream of the compressed air preheating means 17, and a fuel injection nozzle 19 for supplying fuel to the inlet opening 18 ₁ thereof is mounted. Inside the fuel mixing section 18, a plurality of compressed air inlets 18 ₂ formed on the outer periphery of the fuel mixing section 18 and the compressed air introduced from the inlet openings 18 ₁ are mixed with the fuel supplied from the fuel injection nozzle 19 to form a mixture. Is formed.

The air-fuel mixture passes through the swirler 20 and is further uniformly mixed, and then passes through the pair of straightening plates 21 and 22 and is supplied to the catalytic combustion unit 23. The catalyst combustion unit 23 is formed by arranging an upstream side catalyst carrier 24 and a downstream side catalyst carrier 25 formed in a honeycomb shape in series.
A catalyst for burning the air-fuel mixture by a catalytic reaction is carried on the surface of the. The catalyst carriers 24 and 25 are made of a material having a high electric resistance, and the catalyst carriers 24 and 25 themselves constitute catalyst carrier preheating means 26 and 27. Catalyst carrier preheating means 26, 2
7 is energized and generates heat when the gas turbine engine G is started.

Combustion gas passage 15 connected to the catalytic combustion unit 23
The turbine 5 provided at the downstream end of the is composed of a guide vane 28 and a turbine rotor 29, and rotates by the pressure of combustion gas to drive the rotating shaft 3. The exhaust gas that has passed through the turbine 5 is exhaust gas purification catalyst 31 provided in the exhaust gas passage 30.
After passing through, the heat is passed through the heat exchanger 11 and discharged.

An electronic control unit U comprising a microcomputer for controlling the operation of the gas turbine engine G
Is provided. The input circuit of the electronic control unit U includes a catalyst combustion unit inlet air temperature sensor S ₁ for detecting the inlet air temperature of the catalyst combustion unit 23 and a catalyst combustion unit outlet air temperature sensor S for detecting the outlet air temperature of the catalyst combustion unit 23. ₂ , an upstream catalyst carrier temperature sensor S ₃ that detects the temperature of the upstream catalyst carrier 24, a downstream catalyst carrier temperature sensor S ₄ that detects the temperature of the downstream catalyst carrier 25, and the inlet air temperature of the turbine 5 A turbine inlet air temperature sensor S ₅ is connected, and the output circuit is provided with compressed air preheating means 17, upstream side catalyst carrier preheating means 26, and downstream side catalyst carrier preheating means 2.
7, a fuel injection nozzle 19, a solenoid 13 of the bypass valve 14, and a starter 32 for starting which is connected to the rotary shaft 3.
Are connected via the drivers D _{1 to} D ₆ , respectively.

Next, the operation of the embodiment of the present invention having the above construction will be described.

When the gas turbine engine G is in a steady operation state, the air that has passed through the air cleaner 8 and has been sucked into the intake passage 9 is compressed to high temperature and high pressure by the compressor 4 and flows into the front compressed air passage 10, where it is compressed. The rear compressed air passage 1 while passing through the heat exchanger 11 and being heated to a higher temperature
Inflow to 2. In the steady operation state, the bypass valve 14 is held in the open state, and the compressed air that has passed through the bypass valve 14 passes through the compressed air preheating means 17 and the fuel mixing section 18
Is supplied to. In the steady operation state, the compressed air is already heated to the catalyst activation temperature or higher in the compressor 4 and the heat exchanger 11, and the compressed air preheating means 17 is not energized.

The compressed air is mixed with the fuel injected from the fuel injection nozzle 19 in the fuel mixing section 18 to form an air-fuel mixture, which flows into the catalyst combustion section 23 and contacts the catalyst carried on the catalyst carriers 24 and 25. To burn. At this time, the catalyst carrier 24,
The temperature of 25 has already been heated above the catalyst activation temperature, and the catalyst carrier preheating means 26 and 27 are not energized. The combustion gas generated in the catalytic combustion unit 23 is supplied to the gas turbine 5 through the combustion gas passage 15, and the exhaust gas that drives the gas turbine 5 and flows out into the exhaust gas passage 30 is exhaust gas purification catalyst 31 and heat exchange. It passes through the container 11 and is discharged.

Next, a method for starting the gas turbine engine G will be described.

First, in response to a command from the electronic control unit U, the compressed air preheating means 17 and the catalyst carrier preheating means 26,
Energize 27. At this time, since the starter 32 has not been driven yet, the compressed air is not supplied from the compressor 4 to the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27. Therefore, the temperature of the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 itself is rapidly raised by the energization without the heat being taken by the compressed air.

After the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 are energized for a predetermined time, the starter 32 is started by a command from the electronic control unit U. The bypass valve 14 is closed by a command from the electronic control unit U from the start of the starter 32 until the rotation speed thereof reaches a predetermined value. As a result, the compressed air is supplied from the rear compressed air passage 12 to the combustion gas passage 15 via the bypass passage 16 without passing through the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27, and the starter is started. Until 32 starts and the rotation increases
The temperature rise of the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 is not hindered by the compressed air.
Instead of bypassing the compressed air by the bypass valve 14, it is also possible to discharge the compressed air from the compressed air passages 10 and 12 to the outside.

When the rotation speed of the starter 32 reaches a predetermined value, the bypass valve 14 is opened, and the compressed air supplied from the compressor 4 passes through the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27. However, during that time, the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 are continuously energized, and the compressed air temperature and the catalyst carrier temperature further rise. Then, the catalyst combustion unit inlet air temperature sensor S ₁
The inlet air temperature of the catalyst combustion section 23 detected in step S3 becomes equal to or higher than the catalyst activation temperature, and the upstream side catalyst carrier temperature sensor S ₃
And when the temperature of both catalyst carriers 24 and 25 detected by the downstream side catalyst carrier temperature sensor S ₄ becomes equal to or higher than the inlet air temperature, fuel injection from the fuel injection nozzle 19 is started, and at the same time or after a predetermined time, compressed air preheating is performed. Both the means 17 and the catalyst carrier preheating means 26, 27 are de-energized.

The upstream catalyst carrier temperature sensor S₃And below
Flow side catalyst carrier temperature sensor S_FourBoth catalyst carriers detected in 2
Instead of the temperatures of 4, 25, the catalyst combustion unit outlet air temperature sensor
S ₂The outlet air temperature of the catalytic combustion unit 23 detected by
You may stay. That is, the catalyst combustion unit inlet air temperature sensor S₁
The inlet air temperature detected by the
And the catalyst combustion outlet air temperature sensor S₂Detected by
When the outlet air temperature exceeds the inlet air temperature
In addition, the fuel injection from the fuel injection nozzle 19 may be started.
Yes.

Thus, by the preheating, the catalytic combustion unit 23
Since the inlet air temperature of the catalyst and the temperatures of both catalyst carriers 24 and 25 (or the inlet air temperature of the catalyst combustion section 23) are both preheated to the catalyst activation temperature or higher, the air-fuel mixture supplied to the catalyst combustion section 23 becomes a catalyst. The reaction starts combustion, and the gas turbine engine G is started. As described above, by stopping the energization of the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 at the same time as the start of the fuel injection or after a predetermined time, the catalyst generated by the heat generation due to the combustion of the air-fuel mixture and the electric heat generation. It is possible to avoid the overheating and melting loss of the carriers 24 and 25.

Moreover, the compressed air preheating means 17 and the catalyst carrier preheating means 26, 27 are energized prior to the start of the starter 32, and the bypass valve 14 is closed for a predetermined time after the starter 32 is started, whereby the compression is performed. Air preheating means 1
7 and the catalyst carrier preheating means 26, 27 themselves can be quickly raised in temperature, and the time required to start the gas turbine engine G can be greatly shortened.

When the gas turbine engine G is started, the bypass valve 14 is commanded by the electronic control unit U so that the turbine inlet air temperature detected by the turbine inlet air temperature sensor S ₅ is maintained at 400 ° C. or lower.
Is controlled to open and close. That is, the turbine inlet air temperature is 40
When the temperature exceeds 0 ° C., the bypass valve 14 is opened, and compressed air is heated by compressed air preheating means 17 and catalyst carrier preheating means 26, 2.
Bypassing 7 reduces the turbine inlet air temperature to 400 ° C. or less.

The turbine inlet air temperature at startup is 500 to
In a conventional gas turbine engine set at about 1000 ° C, the rotational speed, pressure, air flow rate, etc. tend to fluctuate momentarily before and after ignition, but when a conventional diffusion combustor is used, the stability is stable. There was no problem because the combustion range was wide. On the other hand, since the catalytic combustor has a narrower stable combustion range than the diffusion combustor, misfire or incomplete combustion may occur immediately after ignition. However, by maintaining the turbine inlet air temperature at 400 ° C. or lower as described above and starting the engine, it is possible to suppress variations in various conditions before and after ignition within the combustion range of the catalyst, and to perform stable startup.

By the way, at the time of starting the gas turbine engine G, unburned gas is easily discharged during the period from the ignition to the transition to the steady operation state. It is desirable to shorten to. For that purpose, the inlet air temperature of the catalyst combustion unit 23 and the temperature distribution inside the catalyst carriers 24 and 25 at the time of ignition by preheating may be made to agree with those in the steady combustion state in advance.

FIG. 4 (A) shows the temperature distribution in a steady operation state, the inlet air temperature of the catalyst combustion section 23 is higher than the catalyst activation temperature, and the temperature distribution in the catalyst carriers 24 and 25 is the inlet. It is higher than the air temperature and gradually increases from the upstream side to the downstream side. FIG. 4 (B) shows the temperature distribution immediately before ignition obtained by preheating. The inlet air temperature of the catalyst combustion part 23 and the temperature distributions in the catalyst carriers 24, 25 show the steady operation shown in FIG. 4 (A). It is almost the same as in the state. Here, the temperature distribution in the catalyst carriers 24 and 25 can be obtained as follows.

That is, by making the amount of electricity supplied to the catalyst carrier preheating means 27 of the downstream catalyst carrier 25 larger than the amount of electricity supplied to the catalyst carrier preheating means 26 of the upstream catalyst carrier 24, both catalyst carriers 24, 25 The temperature difference indicated by the broken line is given. When compressed air is supplied to the catalytic combustion section 23 in this state, heat is taken by the compressed air having a temperature lower than the temperatures of the catalyst carriers 24 and 25, and the temperature of the catalyst carriers 24 and 25 is greatly decreased on the upstream side of the catalyst carriers 24 and 25. The temperature gradient shown by the solid line in FIG. 4B can be obtained. Thus, by controlling the energization amount and the compressed air supply amount for the catalyst carriers 24 and 25 arranged in multiple stages, a temperature distribution very close to the temperature distribution in the steady operation state is given in advance, and the steady operation is immediately performed immediately after ignition. It is possible to prevent the discharge of unburned gas by shifting to the state.

FIG. 5 shows a second embodiment of the present invention.

In this embodiment, the catalyst carrier preheating means 26, is provided on the upstream side catalyst carrier 24 and the downstream side catalyst carrier 25 itself.
Instead of providing 27, catalyst carrier preheating means 33, 34 for preheating both catalyst carriers 24, 25 are provided immediately before the entrance of both catalyst carriers 24, 25. When the gas turbine engine G is started, the catalyst carrier preheating means 33, 34 are energized by the command from the electronic control unit U to generate heat, and preheat the temperature of both catalyst carriers 24, 25 to the catalyst activation temperature or higher.

As described above, by providing the catalyst carrier preheating means 33, 34 immediately before the entrance of the catalyst carriers 24, 25,
Catalyst carrier preheating means 26, 27 are provided on the catalyst carriers 24, 25 themselves.
It is possible to prevent spontaneous combustion of the air-fuel mixture that tends to occur when the above is provided. As a result, the catalytic reaction can be started at the same time as the fuel supply, and the steady combustion state can be promptly transitioned to more reliably prevent the unburned gas from being discharged.

FIG. 6 shows a third embodiment of the present invention.

In this embodiment, the downstream side of the catalytic combustion unit 23
The gas-phase combustion unit 35 is provided in the. Inlet of vapor phase combustion section 35
In the gas-phase combustion unit 3 when the gas turbine engine G is started,
Wall surface 5₁Gas-phase combustion for preheating above a specified temperature
A baking part preheating means 36 is provided. Preheating means for vapor phase combustion section 3
6 further heats the compressed air that has passed through the catalytic combustion unit 23.
The vapor phase through its heated compressed air
Wall surface 35 of combustion section 35 ₁Preheat. And Gaster
The temperature of the catalyst carriers 24 and 25 of the bin engine G is catalytically active.
Wall surface 35 of the vapor-phase combustion section 35 that has been preheated to a temperature above
₁Is preheated above a certain temperature by heated compressed air
Therefore, when starting, the wall surface 35₁Temperature of unburned mixture near
And to prevent the reaction from being discharged without completion
Both heat the compressed air that has passed through the catalytic combustion unit 23.
As a result, a steady combustion state of the gas turbine engine G is achieved.
A very close temperature distribution is given. Therefore, this preheating condition
When fuel is supplied from the state to start combustion of the air-fuel mixture,
Eliminates unburned gas emissions by quickly transitioning to a steady combustion state
To be done.

FIG. 7 shows a fourth embodiment of the present invention.

In this embodiment, the wall surface 3 of the vapor-phase combustion section 35 is used.
5 _1, the gas phase combustion portion preheating means 36 for preheating the air in the gas phase combustion portion 35 at the start of the gas turbine engine G is provided. The vapor-phase combustion section preheating means 36 is a gas-phase combustion section 35.
By preheating the wall surface 35 ₁ of the
_{In the} vicinity of ₁ , the temperature of the unburned air-fuel mixture is prevented from lowering and the reaction is prevented from being discharged without being completed, and the compressed air that has passed through the catalytic combustion section 23 is further heated.

Thus, the temperature of the catalyst carriers 24 and 25 of the gas turbine engine G is preheated to the catalyst activation temperature or higher,
And air predetermined temperature of the wall 35 ₁ and the gas phase combustion portion 35 of the gas phase combustion portion 35 (e.g., catalyst activation temperature) by being preheated to above, the temperature distribution very close to a steady combustion state of the gas turbine engine G Is given. Therefore, when the fuel is supplied from this preheated state to start the combustion of the air-fuel mixture, the steady combustion state is promptly transitioned and the discharge of the unburned gas is suppressed.

Although the embodiment of the present invention has been described in detail above, the present invention is not limited to the above embodiment, and various design changes can be made.

[0052]

As described above, according to the invention as set forth in claim 1, there is provided a catalytic combustor for a gas turbine engine equipped with a fuel mixing section, a catalytic combustion section, compressed air preheating means and catalyst carrier preheating means. In the starting method, before starting the combustion by the fuel supply from the fuel injection nozzle, the inlet air temperature of the catalyst combustion section is preheated to the catalyst activation temperature or more, and the temperature of the catalyst carrier or the outlet air temperature of the catalyst combustion section is set to the inlet. By preheating above the air temperature, the inlet air temperature of the catalyst combustion section at the start of combustion and the temperature of the catalyst carrier or the outlet air temperature of the catalyst combustion section are brought to a state close to the temperature distribution in the steady combustion state in advance, and It is possible to promptly shift to a steady combustion state after ignition and suppress the consumption of unburned gas.

According to the invention described in claim 2,
By setting the temperature distribution of the catalyst carrier along the flow direction of the air-fuel mixture so that the downstream temperature is higher than the upstream temperature, the temperature distribution in the steady combustion state is accurately reproduced,
The transition to the steady combustion state can be performed more quickly.

According to the invention described in claim 3,
The catalyst carriers are arranged in multiple stages along the flow direction of the air-fuel mixture,
By setting the temperature of the downstream catalyst carrier to be higher than the temperature of the upstream catalyst carrier, the temperature distribution in the steady combustion state can be easily achieved.

According to the invention described in claim 4,
By controlling the temperature distribution of the catalyst carrier by the amount of electricity supplied to the catalyst carrier preheating means and / or the amount of compressed air supplied to the catalyst carrier, the temperature distribution in the steady combustion state can be reproduced more accurately.

According to the invention described in claim 5,
By disposing the catalyst carrier preheating means immediately before the entrance of the catalyst carrier, the catalyst carrier can be heated while avoiding spontaneous ignition of the air-fuel mixture.

According to the invention described in claim 6,
In a method for starting a catalytic combustor for a gas turbine engine, which includes a fuel mixing section, a catalytic combustion section, and a preheating means, by energizing the preheating means for a predetermined time before starting by the starter, during energization of the preheating means. The time required for starting can be shortened by stopping the supply of compressed air to quickly raise the temperature of the preheating means itself.

According to the invention described in claim 7,
By bypassing and / or extracting the compressed air supplied to the preheating means for a predetermined time after starting by the starter, the supply of the compressed air to the preheating means is suppressed and the temperature of the preheating means itself is quickly increased. However, the starter can be raised to the required number of revolutions to further reduce the time required for starting.

According to the invention described in claim 8,
In a method for starting a catalyst combustor for a gas turbine engine including a fuel mixing section, a catalyst combustion section, and a catalyst carrier preheating means, when the temperature of the catalyst carrier or the catalyst outlet air temperature by the catalyst carrier preheating means reaches a predetermined temperature, By starting the fuel supply from the fuel injection nozzle and stopping the energization to the catalyst carrier preheating means at the same time or after a predetermined time, the temperature distribution in the steady combustion state is quickly achieved and the catalyst carrier is overheated after the start of combustion. Can be suppressed and damage to the catalyst carrier can be prevented.

According to the invention described in claim 9,
In a method for starting a catalytic combustor for a gas turbine engine, which includes a fuel mixing section and a catalytic combustion section, by maintaining an inlet air temperature of the turbine at 400 ° C. or lower at the time of starting,
It is possible to suppress a sudden change in the number of revolutions, pressure, air flow rate, etc. immediately after ignition, stabilize the combustion state, and quickly shift to the steady combustion state.

According to the invention described in claim 10, the ratio of the amount of air passing through the catalytic combustion part and the amount of air bypassing the catalytic combustion part is controlled so that the inlet air temperature of the turbine is 400 ° C. or lower. By holding the temperature, the inlet air temperature can be easily and reliably controlled.

According to the invention described in claim 11, in the method of starting a catalytic combustor for a gas turbine engine having a fuel mixing section and a catalytic combustion section, the engine speed before and after the start of fuel supply is sharply increased. By controlling the starter load so that it does not change, it is possible to reliably start the gas turbine engine.

According to the twelfth aspect of the present invention, in the method for starting a catalytic combustor for a gas turbine engine having a fuel mixing section and a catalytic combustion section, the amount of air passing through the catalyst before and after starting fuel supply is sharp. By controlling the catalyst bypass air amount so that it does not change to, it is possible to reliably start the gas turbine engine.

According to a thirteenth aspect of the present invention, there is provided a method for starting a catalytic combustor for a gas turbine engine, comprising a fuel mixing section, a catalytic combustion section, and a gas phase combustion section.
By providing a means for preheating the air in the gas-phase combustion section, it is possible to cause a gas-phase reaction in the gas-phase combustion section quickly and shift to a steady operation state.

According to the fourteenth aspect of the present invention, the means for preheating the air in the gas-phase combustion section includes a preheater installed upstream of the catalyst, a catalyst heater capable of electrically preheating the catalyst carrier, and immediately after the catalyst. Any one of the installed preheater and the wall surface heater disposed downstream of the catalyst or a combination thereof can reliably preheat the air in the gas phase combustion section.

According to the fifteenth aspect of the present invention, the gas turbine engine is started by preheating the air temperature of the gas phase combustion section or the wall surface temperature downstream of the catalyst to a predetermined temperature and then starting the fuel supply. It is possible to quickly shift to a steady combustion state and suppress the discharge of unburned gas.

[Brief description of drawings]

FIG. 1 is a vertical sectional view of a gas turbine engine.

FIG. 2 is an enlarged view of a main part of FIG.

3 is a sectional view taken along line 3-3 of FIG.

FIG. 4 is a diagram showing a temperature distribution inside a gas turbine engine.

FIG. 5 is a partial view of a gas turbine engine according to a second embodiment.

FIG. 6 is a partial view of a gas turbine engine according to a third embodiment.

FIG. 7 is a partial view of a gas turbine engine according to a fourth embodiment.

[Explanation of symbols]

Reference Signs List 4 compressor 5 turbine 17 compressed air preheating means 18 fuel mixing section 19 fuel injection nozzle 23 catalyst combustion section 24 catalyst carrier 25 catalyst carrier 26 catalyst carrier preheating means 27 catalyst carrier preheating means 32 starter 33 catalyst carrier preheating means 34 catalyst carrier preheating means 35 Gas-phase combustion part 35 ₁ Wall surface 36 Gas-phase combustion part preheating means

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Takashi Sakauchi 1-4-1 Chuo, Wako-shi, Saitama Inside the Honda R & D Co., Ltd. (72) Inventor Eiichi Utsuki 1-4-1 Chuo, Wako-shi, Saitama No. Incorporated in Honda R & D Co., Ltd. (72) Inventor Ken Ken Oya 1-4-1 Chuo, Wako-shi, Saitama Incorporated in Honda R & D Co., Ltd. (72) Naomi Warashina 1-4-1 Chuo, Wako, Saitama No. Incorporated in Honda R & D Co., Ltd. (72) Hidemi Kimura 1-4-1, Chuo, Wako-shi, Saitama Incorporated in Honda R & D Co., Ltd. (72) Hidehiko Nakata 1-4, Wako-Chu, Saitama No. 1 Stock Company Honda Technical Research Institute

Claims (15)

[Claims] 1. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. A catalyst combustion part (23) for combusting the catalyst by a catalytic reaction, a compressed air preheating means (17) capable of electrically preheating the compressed air, and a catalyst carrier (24, 25) of the catalyst combustion part (23). In a method of starting a catalytic combustor for a gas turbine engine, which comprises a catalyst carrier preheating means (26, 27; 33, 34) capable of preheating with heat, before starting combustion by fuel supply from a fuel injection nozzle (19), While preheating the inlet air temperature of the catalyst combustion section (23) to the catalyst activation temperature or higher, the catalyst carrier (24, 25)
Or the outlet air temperature of the catalytic combustion part (23) is preheated to the inlet air temperature or higher, the method for starting a catalytic combustor for a gas turbine engine. 2. A catalyst carrier (2) along the flow direction of the air-fuel mixture.
4, 25) is set so that the temperature on the downstream side is higher than the temperature on the upstream side.
A method for starting a catalytic combustor for a gas turbine engine as described above. 3. The catalyst carriers (24, 25) are arranged in a plurality of stages along the flow direction of the air-fuel mixture, and the catalyst carriers (2) on the downstream side are arranged.
The method for starting a catalytic combustor for a gas turbine engine according to claim 2, wherein the temperature of 5) is set to be higher than the temperature of the catalyst carrier (24) on the upstream side. 4. The temperature distribution of the catalyst carrier (24, 25)
Amount of electricity supplied to catalyst carrier preheating means (26, 27) and /
Alternatively, the method of starting a catalytic combustor for a gas turbine engine according to claim 2, wherein the method is controlled by the amount of compressed air supplied to the catalyst carrier (24, 25). 5. The method for starting a catalytic combustor for a gas turbine engine according to claim 1, wherein the catalyst carrier preheating means (33, 34) is arranged immediately before the inlet of the catalyst carrier (24, 25). . 6. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. Catalyst combustion section (23) for combusting air by catalytic reaction and preheating means (17, 26, 27) capable of electrically preheating the compressed air and / or the catalyst carrier (24, 25) of the catalyst combustion section (23). In the method for starting a catalytic combustor for a gas turbine engine, the preheating means (17, 26, 27) is energized for a predetermined time before the start by the starter (32). For starting a catalytic burner for automobiles. 7. The compressed air supplied to the preheating means (17, 26, 27) is bypassed and / or bleeded for a predetermined time after the start of the starter (32). A method for starting a catalytic combustor for a gas turbine engine. 8. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. And a catalyst carrier (2) of the catalyst combustion unit (23) for combusting
4, 25) for electrically preheating catalyst carrier preheating means (2
In the method for starting a catalyst combustor for a gas turbine engine, the catalyst carrier preheating means (26, 27) comprises
4, 25) or the catalyst outlet air temperature reaches a predetermined temperature, fuel supply from the fuel injection nozzle (19) is started, and at the same time or after a predetermined time, to the catalyst carrier preheating means (26, 27). Characterized by stopping energization,
A method for starting a catalytic combustor for a gas turbine engine. 9. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. A catalytic combustor for a gas turbine engine, comprising: a catalytic combustion part (23) for combusting a gas by a catalytic reaction, characterized in that an inlet air temperature of the turbine (5) is maintained at 400 ° C. or lower at the time of starting. A method for starting a catalytic combustor for an engine. 10. The inlet air temperature of the turbine (5) is maintained at 400 ° C. or lower by controlling the ratio of the amount of air passing through the catalytic combustion unit (23) and the amount of air bypassing the catalytic combustion unit (23). The method for starting a catalytic combustor for a gas turbine engine according to claim 9, wherein 11. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. In a method of starting a catalytic combustor for a gas turbine engine, which comprises a catalytic combustion unit (23) for combusting a gas by a catalytic reaction, controlling the starter load so that the engine speed before and after the start of fuel supply does not suddenly change. A method for starting a catalytic combustor for a gas turbine engine, which is characterized. 12. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. In a method for starting a catalytic combustor for a gas turbine engine, which comprises a catalytic combustion unit (23) for combusting a gas by a catalytic reaction, the amount of catalyst bypass air is controlled so that the amount of air passing through the catalyst does not change rapidly before and after the start of fuel supply. A method for starting a catalytic combustor for a gas turbine engine, comprising: 13. A fuel mixing section (18) in which compressed air supplied from a compressor (4) and fuel supplied from a fuel injection nozzle (19) are mixed, and a mixture composed of the compressed air and the fuel. Catalyst combustor for gas turbine engine, comprising a catalytic combustion part (23) for combusting gas by catalytic reaction, and a gas phase combustion part (35) for combusting air-fuel mixture by gas phase reaction downstream of the catalytic combustion part (23) The starting method of the catalytic combustor for a gas turbine engine, characterized in that it has means (36) for preheating the air in the gas phase combustion section (35). 14. A preheater, wherein a means (36) for preheating the air of the vapor phase combustion section (35) is installed upstream of the catalyst,
14. A catalyst heater capable of electrically preheating the catalyst carrier (24, 25), a preheater installed immediately after the catalyst, or a wall heater arranged downstream of the catalyst, or a combination thereof. For starting a catalytic combustor for a gas turbine engine of the above. 15. The gas turbine engine according to claim 13, wherein fuel supply is started after preheating the air temperature of the gas-phase combustion section (35) or the wall surface temperature downstream of the catalyst to a predetermined temperature. For starting a catalytic burner for automobiles.