JPH10159551A - Engine with catalyst and gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an engine with catalyst and gas turbine in which a catalytic treatment device separate from the engine or the gas turbine is unnecessitated and a concentration control of waste gas components such as NOx and CO in exhaust gas is easily performed also at the time of a maximum output. SOLUTION: This engine is constituted to burn mixed air of compressed air compressed by a compressor and fuel supplied from a fuel injection valve in a combustor at the poststage of the compressor and to revolve a turbine with the combustion gas. In this case, a waste gas decomposition catalytic layer C is formed to decompose/reduce waste gas components such as NOx and CO in combustion gas, on the full surfaces of a turbine stator blade 13 and a turbine rotor blade 14 at the poststage of the combustor or the full surfaces of the turbine stator blade 13 and the turbine rotor blade 14 and the full surface of the inside of a casing of the turbine.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a jet engine and gas turbine aircraft, in particular, it relates to a catalyst with an engine and a gas turbine to reduce the waste gas components such as NO _X and CO.

[0002]

BACKGROUND OF THE INVENTION In aircraft engines (jet engine) and a gas turbine, in order to reduce the waste gas components such as NO _X and CO in exhaust gas, causing the mixture of the compressed air and fuel is combusted in the combustor In order to minimize the generation of the waste gas component itself in the combustion gas generated as a result, a lean fuel is used, or the combustion gas containing the waste gas component is passed through a separately provided catalyst treatment device.

[0003]

However, in an aircraft engine, a catalyst treatment device cannot be separately provided because it is inevitably desired to be light in weight, and the NO. _Although the waste gas components such as _X and CO are reduced, it is difficult to control the numerical value (concentration) of the waste gas components such as NO _X and CO when the highest output is prioritized. Further, like in the ground gas turbine, although reduced waste gas components such as NO _X and CO in the exhaust gas by passing the combustion gas to the catalyst apparatus, to or causing the output reduction, prevent this Therefore, the post-processing becomes large and causes an increase in cost.

Accordingly, the present invention solves the above-mentioned problems, does not require a catalyst treatment apparatus separate from an engine or a gas turbine, and has a high concentration of waste gas components such as NO _X and CO in exhaust gas even at the maximum output. An object of the present invention is to provide a catalyst-equipped engine and a gas turbine that can be easily controlled.

[0005]

According to a first aspect of the present invention, an air-fuel mixture of compressed air compressed by a compressor and fuel supplied from a fuel injection valve is provided at a subsequent stage of the compressor. In an aircraft engine that burns in a combustor and rotates a turbine with the combustion gas, the entire surface of the turbine vanes and turbine blades at the subsequent stage of the combustor, or the entire surface of the turbine vanes, turbine blades, and the inside of the casing of the turbine. it is obtained by forming a waste gas decomposition catalyst layer in order to decompose and reduce the waste gas components such as NO _X and CO in the combustion gases.

[0006] The invention according to claim 2, wherein the said waste gas decomposing catalyst layer for decomposing and reducing the NO _X is vanadium, cobalt, iron, rhodium, consisting of one or a mixture of two or more selected from ruthenium Item 2. A catalyst-equipped engine according to Item 1.

The invention according to claim 3 is the catalyst-equipped engine according to claim 1, wherein the waste gas decomposition catalyst layer for decomposing and reducing the CO is made of platinum, palladium, or a mixture thereof.

According to a fourth aspect of the present invention, a catalyst powder is formed by supporting a waste gas decomposition catalyst on a carrier such as zirconia, and the catalyst powder is applied to the entire surface of the turbine stationary blade and the turbine rotor blade and the entire inner surface of the turbine casing. The catalyst-equipped engine according to any one of claims 1 to 3, wherein the waste gas decomposition catalyst layer is formed by plasma spraying the catalyst.

According to a fifth aspect of the present invention, there is provided a gas turbine for rotating a turbine with combustion gas, wherein the entire surface of the turbine stationary blade and the turbine moving blade, or the entire surface of the turbine stationary blade and the turbine moving blade and the entire inner surface of the turbine casing are provided. A waste gas decomposition catalyst layer is formed to decompose and reduce waste gas components such as NO _X and CO in the combustion gas.

According to the above construction, a mixture of the compressed air compressed by the compressor and the fuel supplied from the fuel injection valve is burned in the combustor at the subsequent stage of the compressor, and the combustion gas rotates the turbine. In the aircraft engine to be driven, the entire surface of the turbine vanes and turbine blades at the subsequent stage of the combustor, or
The turbine vanes and turbine blades of the entire surface and the turbine casing entire inner surface, because the formation of the waste gas decomposing catalyst layer in order to decompose and reduce the waste gas components such as NO _X and CO in the combustion gas, an engine or a gas turbine It is possible to obtain an engine and a gas turbine with a catalyst that do not require a separate catalyst treatment device and that can easily control the concentration of waste gas components such as NO _X and CO in exhaust gas even at the time of maximum output.

[0011]

Embodiments of the present invention will be described below.

FIG. 2 shows an example of a cross-sectional view of a catalyst-equipped engine of the present invention. FIG. 3 is an enlarged view of a main part in FIG.

As shown in FIGS. 2 and 3, the engine 1 with a catalyst according to the present invention comprises an inlet guide vane 7, a compressor 3, a combustor 4, a turbine 5, and a shaft 15. Entrance guide wing 7,
The compressor 3 and the turbine 5 are connected via a shaft 15.

The casing 3 for taking in the air A ₁
air inlet 8 formed at the tip (the left end in the figure)
Is provided with an inlet guide vane 7, and a shaft 15 is provided in connection with the inlet guide vane 7.

The compressor 3 which compresses the air A ₁ introduced from the air inlet 8 into compressed air A ₂ comprises a casing 3
a, an inner casing 3b, a shaft 15, a compressor rotor blade 9, and a compressor stationary blade 10, which are connected to the downstream side (right side in the figure) of the inlet guide blade 7.

The inner casing 3 surrounds the shaft 15.
b, and a casing 3a is provided so as to surround the inner casing 3b. Connected to the shaft 15, a plurality of compression blades 9 are provided radially along the circumferential direction and in multiple stages (seven stages in the figure) along the longitudinal direction. Each compressed rotor blade 9
Has a penetrating inner casing 3b and is rotatable. Inside the casing 3a, a plurality of compression stationary blades 10 are provided radially along the circumferential direction and in multiple stages (six in the figure) over the longitudinal direction. Each compressed rotor blade 9
The compression vanes 10 are alternately arranged along the longitudinal direction of the compressor 3.

A combustor 4 for injecting the fuel F into the compressed air A ₂ supplied from the compressor 3 and burning the fuel F is provided so as to surround the periphery of the shaft 15. To the right). The combustor 4 includes a fuel injection valve 11 for injecting the fuel F into the combustor 4.

The turbine 5 to rotate the turbine blades 14 in the combustion gas G ₁ generated by the combustor 4, the casing 5
a, inner casing 5b, shaft 15, turbine vane 13,
The turbine rotor 14 is connected to a downstream side (right side in the figure) of the combustor 4 via a turbine nozzle 12.

The inner casing 5 surrounds the shaft 15.
b, and a casing 5a is provided so as to surround the inner casing 5b. Connected to the shaft 15, a plurality of turbine blades (for example, Inconel 718, IN600, etc.) 14 are provided radially along the circumferential direction and in multiple stages (three stages in the figure) along the longitudinal direction. . The tip of each turbine blade 14 penetrates the inner casing 5b and is rotatable. A plurality of turbine vanes (for example, Inconel 718, IN60) are provided inside the casing 5a.
0) 13 are provided radially along the circumferential direction and in multiple stages (two stages in the figure) over the longitudinal direction. Each turbine rotor blade 14 and each turbine stationary blade 13 are alternately arranged along the longitudinal direction of the turbine 5. A cone 16 is connected to an end (right end in the figure) of the shaft 15, and a rear end (right end in the figure) of the casing 5 a of the turbine 5 is for discharging exhaust gas G _2. A jet nozzle 6 is formed.

FIG. 1 is a perspective view of a turbine section of an engine with a catalyst according to the present invention.

As shown in FIG. 1, the entire surface of the turbine moving blade 14 and the turbine stationary blade 13, or the entire surface of the turbine moving blade 14 and the turbine stationary blade 13 and the casing 5 of the turbine 5.
The a entire inner surface, a waste gas decomposing catalyst layer C to decompose and reduce the waste gas components such as NO _X and CO in the combustion gas G ₁ is formed.

The waste gas decomposition catalyst layer C for decomposing and reducing NO _X is composed of one or a mixture of two or more selected from vanadium, cobalt, iron, rhodium and ruthenium, and decomposes and reduces CO. The waste gas decomposition catalyst layer C is made of platinum or palladium, or a mixture thereof.

The waste gas decomposition catalyst layer C only needs to be coated (adhered) to the extent that it is worn by erosion due to fine particles in the air, and it is sufficient if there is even an overhaul that is performed periodically. The film thickness is several μ
About m to several tens μm is sufficient.

[0024] The waste gas components such as NO _X and CO in the combustion gas G _1, there is an optimum temperature to remove each, NO _X
Is about 600-1,200 ° C., and about 400 ° C. or more for CO. Therefore, during the formation of the waste gas decomposing catalyst layer C must take into account the temperature distribution inside the turbine 5, a waste gas decomposition catalyst for NO _X is upstream of the turbine 5 than the waste gas decomposition catalyst for CO It is preferable to form it on the side (left side in the figure).

The coating (forming) of the waste gas decomposition catalyst layer C in the present invention is preferably performed by plasma spraying, but is not particularly limited thereto.
It goes without saying that CVD, coating and baking (sol-gel method) may be used.

Next, the operation of the present invention will be described.

The inlet guide vanes 7 in front of the catalyzed engine 1 are started, and air A ₁ is introduced into the compressor 3 from the air intake 8. As the entrance guide vanes 7 rotate, the shaft 15 connected to the entrance guide vanes 7 rotates. The air A ₁ introduced into the compressor 3 is compressed by the compressor rotor blades 9 and the compressor vanes 10 rotating together with the shaft 15 and compressed air A _2.
Becomes

The compressed air A ₂ is supplied into the combustor 4 and mixed with the fuel F supplied from the fuel injection valve 11 to form an air-fuel mixture (not shown). This air-fuel mixture is burned to produce a combustion gas G ₁ , which is supplied to the turbine 5 via the turbine nozzle 12.

The combustion gas G ₁ is applied to the turbine rotor blades 14 to rotate the shaft 15, rotate the inlet guide vanes 7 connected to the shaft 15, and supply new air A ₁ to the compressor 3.
Introduce one after another inside. Thereafter, the combustion gas G _1, is discharged from the jet nozzle 6 as an exhaust gas G _2.

Inside the turbine 5, the combustion gas G ₁ is rectified by a turbine rotor blade 14 and a turbine stationary blade 13 in order to improve the rotation efficiency of the turbine 5. That is, the combustion gas G ₁ is controlled so as to flow along a flow path (not shown) formed by the turbine rotor blades 14 and the turbine stationary blades 13, and the combustion gas G ₁ , the turbine rotor blades 14 and The contact with the turbine vane 13 is originally good.

In order to make good use of the good contact between the combustion gas G ₁ and the turbine rotor blades 14 and the turbine stator blades 13, the entire surfaces of the turbine rotor blades 14 and the turbine stator blades 13 or the turbine rotor blades 14 and the turbine stator blades 13 are used. the casing 5a entire inner surface of the entire surface and the turbine 5 of 13 to form a waste gas decomposition catalyst layer C, thereby decomposing and reducing waste gas components such as NO _X and CO in the combustion gas G _1.

That is, vanadium, cobalt, and the like (eg, zirconia)
A porous catalyst powder is formed by supporting a waste gas decomposition catalyst such as iron, rhodium, ruthenium, platinum, or palladium, and this porous catalyst powder is mixed with the turbine blade 14 before assembly.
And the entire surface of the turbine stationary blade 13 or the turbine rotor blade 14
Then, plasma spraying is performed on the entire surface of the turbine vane 13 and the entire inner surface of the casing 5 a of the turbine 5. This makes it possible to form a waste gas decomposition catalyst layer C that can simultaneously perform heat shielding and removal of waste gas components such as NO _X and CO in the combustion gas G ₁ .

[0033] Here, unlike the surface smooth coated compressor rotor blades 9 and the compressor stator blades 10 in order to introduce air A ₁ efficiently, on the entire surface of the turbine stator blades 13 and turbine blades 14 , Thermal barrier coating with a thickness of about 100-200 μm (Zr, M-CrAlY (M-Clary)
And the like, and the surface condition of the turbine stationary blade 13 and the turbine rotor blade 14 is rough. Therefore, the surface state (smoothness) of the turbine stator blades 13 and turbine rotor blades 14 is not very severe, the waste gas decomposing catalyst layer C there is little that affect the flow of combustion gases G _1.

Next, another embodiment of the present invention will be described.

In the present invention, the waste gas cracking catalyst layer C is formed on the entire surface of the turbine stationary blades 13 and the turbine blades 14 and on the entire inner surface of the casing 5a of the turbine 5. Needless to say, the formation may be performed only by the turbine stationary blades 13 and the turbine rotor blades 14, whereby the amount of the waste gas decomposition catalyst used can be reduced, and the production cost can be reduced.

[0036] In the present invention, although the waste gas decomposition catalyst layer C for waste gas decomposition catalyst layer C and CO for NO _X formed separately, the waste gas decomposition catalyst for NO _X and CO A catalyst powder is formed by mixing the catalyst powder with a waste gas cracking catalyst for use and supporting it together with a carrier to form the catalyst powder. May be uniformly applied by plasma spraying. As a result, the waste gas decomposition catalyst layer C capable of simultaneously performing heat shielding and removing waste gas components in the combustion gas G _1.
Can be formed in a single step, and the manufacturing time and manufacturing steps can be significantly reduced.

Further, in the present invention, the waste gas cracking catalyst layer C is applied to the engine 1 with a catalyst, but the waste gas cracking catalyst layer C may be applied to a gas turbine (not shown). Needless to say. Thus, compared to when the combustion gas G ₁ was passed through the catalytic treatment device (not shown) to reduce the waste gas components such as NO _X and CO in the exhaust gas G _2, it requires less output decreases. For this reason, the post-processing for preventing the output from decreasing does not become large-scale, and the increase in cost can be suppressed.

[0038]

In summary, according to the present invention, since a waste gas decomposition catalyst layer is formed on the inner surface of an engine or a gas turbine, a catalyst treatment device separate from the engine or the gas turbine is not required, and the maximum output is achieved. also is easy density control of the waste gas components such as NO _X and CO in the exhaust gas at the time, and it is possible to perform the decomposition and reduction of the waste gas components in the combustion gas, the thermal barrier of the hot combustion gases Can be performed.

[Brief description of the drawings]

FIG. 1 is a perspective view of a turbine section of an engine with a catalyst according to the present invention.

FIG. 2 is a view showing an example of a cross section of the engine with a catalyst of the present invention.

FIG. 3 is an enlarged view of a main part in FIG. 2;

[Explanation of symbols]

With 1 catalytic engine 3 compressor 4 combustor 5 turbine 5a casing 11 fuel injection valve 13 turbine vane 14 turbine blade A ₁ air A ₂ compressed air F fuel G ₁ combustion gas G ₂ exhaust C waste gas decomposition catalyst layer

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code FI B01J 23/46 311 F01D 9/02 ZAB 23/745 101 23/75 F01N 3/10 ZABZ F01D 5/14 ZAB F02C 7/00 E 9/02 ZAB C 101 ZABF F01N 3/10 ZAB 9/00 ZABA F02C 7/00 B01D 53/36 ZAB 102D ZAB 103B 9/00 ZAB B01J 23/74 301A 311A

Claims (5)

[Claims] 1. An aircraft engine in which a mixture of compressed air compressed by a compressor and fuel supplied from a fuel injection valve is burned in a combustor at a subsequent stage of the compressor, and the combustion gas rotates a turbine. the combustor downstream of the turbine vanes and turbine blades of the entire surface, or, the turbine vanes and turbine blades of the entire surface and the casing inner entire surface of the turbine, the waste gas components such as NO _X and CO in the combustion gas An engine with a catalyst characterized by forming a waste gas decomposition catalyst layer to decompose and reduce it. 2. The catalyst according to claim 1, wherein the waste gas decomposition catalyst layer for decomposing / reducing NO _{x comprises} one or a mixture of two or more selected from vanadium, cobalt, iron, rhodium and ruthenium. With engine. 3. The engine with a catalyst according to claim 1, wherein the waste gas decomposition catalyst layer for decomposing and reducing the CO is made of platinum, palladium, or a mixture thereof. 4. A catalyst, such as zirconia, having a waste gas decomposition catalyst supported thereon to form a catalyst powder, and the catalyst powder is subjected to plasma spraying on the entire surfaces of the turbine stationary blade and the turbine rotor blade and on the entire inner surface of the turbine casing. The catalyst-equipped engine according to any one of claims 1 to 3, wherein the waste gas decomposition catalyst layer is formed. 5. A gas turbine for rotating a turbine with combustion gas, wherein the entire surface of a turbine stationary blade and a turbine rotor blade is provided.
Or, the turbine vanes and turbine blades of the entire surface and the casing inner entire surface of the turbine, NO _X in the combustion gases
A gas turbine with a catalyst, comprising a waste gas decomposition catalyst layer formed to decompose and reduce waste gas components such as CO and CO.