JPH07224683A - Support device for high-temperature part in engine for aircraft - Google Patents

Abstract

PURPOSE:To provide such a support device for a high-temperature part in an engine for an aircraft that prevents so-called electrolytic corrosion of the high- temperature part so as to improve durability. CONSTITUTION:A support device for a high-temperature part is provided with a cylindrical burner duct, a high-temperature part (a frame holder 14) arranged in the burner duct, and a support part 16 for supporting the high-temperature part in the burner duct, the burner duct and the support part are formed of metal materials, the high-temperature part is formed of a material having heat resistance, and a ceramic part (a sleeve 18) is interposed between the high- temperature part and the support part. It is preferable that the burner duct and the support part are formed of high nickel radical alloy and the high- temperature part is formed of silicon carbide or silicon nitride.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for supporting a high temperature component (for example, a frame holder) in an aircraft engine (for example, a ramjet engine). Except the support device).

[0002]

2. Description of the Related Art Although a conventional ramjet engine does not have an air compressor such as a gas turbine, the ram pressure is used to compress the air flowing into the combustor duct at high speed. Cage, simple structure,
Moreover, it is considered that the combustion efficiency can be improved as the navigation speed of the airframe increases, and for example, the Mach number is 2.5.
Application of cruising speeds of ~ 5 to supersonic aircraft and space shuttles has been studied.

FIG. 7 shows a schematic structure of a ramjet engine. Reference numeral 1 is a diffuser, 2 is a combustor duct, 3 is a combustion chamber, 4 is a jet nozzle, and 5 is a ram combustion device. The ram combustion device 5 has a structure in which high-temperature parts such as a fuel nozzle and a frame holder are attached to and held by a fastener such as a bolt at the tip of a rod-shaped support part made of a heat-resistant alloy protruding from the inner surface of the combustor duct 2. There is.

[0004]

By the way, in the ramjet engine, since the temperature inside the combustion chamber 3 is 1000 ° C. or higher, high temperature parts such as the fuel nozzle and the frame holder are required to have high heat resistance. It is conceivable that the high temperature component is formed of silicon carbide or silicon nitride having high heat resistance.

However, when the high temperature parts such as the fuel nozzle and the frame holder are made of silicon carbide or silicon nitride as described above, the high temperature parts and the supporting parts are in direct contact with each other and are supported by a metal in a high temperature atmosphere. The parts may act as a kind of catalyst, and a phenomenon such as so-called electrolytic corrosion may occur in which high-temperature parts such as the frame holder are melted at the contact portions, which may cause deterioration of durability.

The present invention has been made in view of the above circumstances, and an object thereof is to provide a device for supporting high temperature components in an aircraft engine, which can prevent so-called electrolytic corrosion of high temperature components and enhance durability. To do.

[0007]

SUMMARY OF THE INVENTION A support device of the present invention comprises a tubular combustor duct, a high temperature component arranged in the combustor duct, and a support component for supporting the high temperature component in the combustor duct. A support device for a high-temperature component in an aircraft engine, comprising: the combustor duct and the support component made of a metal material; the high-temperature component made of a heat-resistant material; A ceramic component is interposed between the support component and the support component.

It is preferable that the combustor duct and the supporting component are made of a high nickel base alloy, and the high temperature component is made of silicon carbide or silicon nitride.

[0009]

According to the supporting device of the present invention, since the ceramic component is interposed between the high temperature component and the supporting component, the high temperature component and the supporting component do not come into direct contact with each other, and the high temperature component is carbonized, for example. Even if the support component is made of silicon or silicon nitride and the support component is made of, for example, a high nickel-based alloy, the so-called electrolytic corrosion phenomenon is reliably prevented, and the durability of the device is significantly improved.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A supporting device according to an embodiment of the present invention will be described below with reference to the drawings.

FIG. 1 is a cross-sectional view of a ram combustion device for a ramjet engine, in which 12 is a combustor duct, 13 is a combustion chamber, and 14 is a composite material made of silicon carbide or silicon nitride, which is a high temperature component of the present invention. Of the frame holder, 15 is a gutter having a substantially V-shaped cross section protruding from the inner peripheral surface and the outer peripheral surface of the frame holder 14, and 16 is a rod-shaped support component made of a high nickel-based alloy,
Reference numeral 17 is a bolt and nut (fastener, made of metal) for connecting the frame holder 14 to the support component 16, and 18 is a sleeve (ceramic component) interposed between the frame holder 14 and the support component 16. .

FIG. 2 shows the frame holder 14 and the supporting member 16
The enlarged view of the connection part with is shown.

A plurality of protrusions 14a are formed on the end surface of the frame holder 14 at predetermined intervals in the circumferential direction.
As shown in FIG. 2, these protrusions 14a have through holes 1
4b is formed. On the other hand, the tip of the support component 16 is branched into a bifurcated shape, and these branch portions 16a are arranged so as to sandwich the projecting portion 14a.
A through hole 16b is formed in 6a corresponding to the protruding portion 14a.

Then, one through hole 16 of the support component 16 is formed.
The bolt 17a is attached to the through hole 14 of the frame holder 14 from b.
It is inserted in a and protrudes through the other through hole 16b, and a nut 17b is screwed and tightened at the protruding end.

The linear expansion coefficient of nickel alloy is the largest, the linear expansion coefficient of silicon carbide is the second largest, and the linear expansion coefficient of ceramic is the smallest. As a result, even if the temperature rises after tightening, the sleeve 18 is securely fixed to the frame holder 14 and the support component 16 without being loosened and loosened.

Here, on the outer peripheral surface of the bolt 17a, a sleeve 18 in which a disk-shaped flange portion 18a is formed at both ends of a cylindrical portion 18b is inserted, and when the bolt 17a and the nut 17b are tightened, The tubular portion 18 of the sleeve 18
b is inserted into the through hole 14b of the frame holder 14,
The flange portion 18a is the protrusion portion 14a of the frame holder 14.
And the branch portion 16a of the support component 16 are interposed and sandwiched.

As described above, in this embodiment, the ceramic sleeve 18 is interposed between the frame holder 14 made of a silicon carbide or silicon nitride composite material and the support component 16 made of a high nickel base alloy, and both of them are provided. Is electrically non-contact. Therefore, even if the atmosphere becomes 1000 ° C. or higher due to combustion, it is possible to prevent an electric current from being generated between the frame holder 14 and the support component 16, and thus to prevent electrolytic corrosion of the frame holder 14 in advance. . As a result, the durability of the ramjet engine, which is an aircraft engine, can be dramatically improved.

Next, a supporting device of another embodiment of the present invention will be described with reference to FIG. The same components as those in the above embodiment will be described with the same reference numerals.

This one uses the following sleeve 28 instead of the sleeve 18 of the above-mentioned embodiment. That is, the sleeve 28 is made of ceramics, as in the above-described embodiment, and includes a tubular portion 28b having a flange portion 28a formed at one end, and a flange portion 28c formed separately from the tubular portion 28b. It is configured with. Here, the flange portion 28c is formed with a through hole 28d into which the end portion of the tubular portion 28b is inserted, and the through hole 28d.
Is slightly larger than the tubular portion 28b.

In this embodiment, the bolt 17a and the nut 17 are
When tightened with b, the tubular portion 28b of the sleeve 28 is inserted into the through hole 14b of the frame holder 14, and the flange portions 28a and 28c are protruded portions 14 of the frame holder 14.
It is interposed and sandwiched between a and the branch portion 16a of the support component 16. Therefore, as in the above-described embodiment, these are electrically non-contact with each other, and so-called electrolytic corrosion of the frame holder 14 can be prevented.

Further, in this embodiment, the flange portion 28c is formed separately from the tubular portion 28b, and the through hole 28d formed in the flange portion 28c is formed larger than the tubular portion 28b and penetrates. Since a slight gap is formed between the hole 28d and the tubular portion 28b, even if the sleeve 28 and the like thermally expand when the temperature rises, the amount of thermal expansion can be absorbed by the gap. Damage to the sleeve 28 due to thermal expansion can be eliminated.

Next, FIG. 4 shows a sleeve 38 used in a supporting apparatus according to still another embodiment of the present invention. The sleeve 38 has a cylindrical portion 3 having a flange portion 38a formed at one end.
8b and a tubular portion 3 which is inserted inside the tubular portion 38b and has a flange portion 38c formed at the end opposite to the insertion end.
8d.

Even in this case, if the sleeve 38 is interposed between the frame holder 14 and the support component 16, they are electrically non-contact with each other, so that so-called electrolytic corrosion of the frame holder 14 can be prevented, and Since the tubular portion 38b and the tubular portion 38d can move relative to each other in the axial direction and the radial direction, damage to the sleeve 38 due to thermal expansion can be prevented.

Next, FIG. 5 shows a sleeve 48 used in a supporting apparatus according to still another embodiment of the present invention. The sleeve 48 includes a half-split cylindrical portion 48b having a flange portion 48a formed at one end and a half split cylindrical portion 48d having a flange portion 48c formed at one end.

In this structure, the half-split cylindrical portion 48b and the half-split cylindrical portion 48d are opposed to each other at the half-split portion, and a slight gap is formed in the half-split portion to form a tubular shape, and the frame holder 14 and the support component 16 are provided. If they are interposed between and, they become electrically non-contact, so that so-called electrolytic corrosion of the frame holder 14 can be prevented, and the half-split cylindrical portions 48b and 48d are axially and The relative movement in the circumferential direction can prevent damage to the sleeve 38 due to thermal expansion.

Next, FIG. 6 shows a supporting device according to still another embodiment of the present invention. It should be noted that the same components as those in the above-described embodiment are designated by the same reference numerals for description.

This is one in which the frame holder 14 is supported by a rod-shaped support component 26. That is, the support component 26 has a so-called double pipe structure in which the inner pipe 26b is inserted inside the outer pipe 26a.
The tip of the outer tube 26 is closed by a plug 26c.
The vicinity of the tip portion of a is formed thick, and a male screw portion 26d is formed on the outer surface thereof. And the support component 2
The sleeve 58 having a tubular portion 58b having a flange portion 58a formed at one end is inserted into the tip portion of the support member 6 to support the support component 2
The front end of 6 is inserted into the through hole 14b formed in the protrusion 14a of the frame holder 14, and the nut 26f is screwed into the male screw portion 26d and tightened.

In this structure, the sleeve 58 is interposed between the frame holder 14 and the support component 26 so that they are electrically non-contact with each other. Food can be prevented in advance. Further, since the support component 26 has a double pipe structure, the cooling water is supplied from the inner pipe 26b and discharged from between the outer pipe 26a and the inner pipe 26b, so that the support component 26
Cooling can be performed, and the support component 26 can be formed of a metal material having relatively low heat resistance.

In the above embodiment, the frame holder 1
Although the supporting device for supporting No. 4 is shown, it is needless to say that the supporting device for supporting No. 4 can also be applied to the case of supporting other high temperature parts supporting the fuel nozzle and the spark plug.

[0030]

As described above, according to the supporting apparatus of the present invention, the cylindrical combustor duct, the high temperature component arranged in the combustor duct, and the high temperature component are provided in the combustor duct. A supporting device for a high temperature component in an aircraft engine, comprising a supporting component for supporting, wherein the combustor duct and the supporting component are formed of a metal material, and the high temperature component is formed of a heat resistant material, and Since the ceramic component is interposed between the high temperature component and the support component, the high temperature component and the support component do not come into direct contact with each other, and the high temperature component is formed of, for example, silicon carbide or silicon nitride, and is supported. Even if the component is made of, for example, a high nickel-based alloy, the so-called electrolytic corrosion phenomenon can be reliably prevented, and the durability of the device can be significantly improved.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing a support device for high temperature components in an aircraft engine according to an embodiment of the present invention.

FIG. 2 is an enlarged cross-sectional view showing a main part of the supporting device of FIG.

FIG. 3 is a sectional view showing a supporting device of another embodiment of the present invention.

FIG. 4 is a sectional view showing a sleeve used in a supporting device according to still another embodiment of the present invention.

FIG. 5 is a perspective view showing a sleeve used in a supporting device according to still another embodiment of the present invention.

FIG. 6 is a sectional view showing a supporting device according to still another embodiment of the present invention.

FIG. 7 is a sectional view showing a schematic configuration of a ramjet engine which is a conventional aircraft engine.

[Explanation of symbols]

 12 Combustor duct 13 Combustion chamber 14 Frame holder 14a Projection part 16,26 Supporting part 17a Bolt 17b Nut 18,28,38,48,58 Sleeve

Claims (2)

[Claims] 1. A high temperature component for an aircraft engine comprising a tubular combustor duct, a high temperature component arranged in the combustor duct, and a supporting component for supporting the high temperature component on the combustor duct. A supporting device, wherein the combustor duct and the supporting component are made of a metal material, the high temperature component is made of a material having heat resistance, and a ceramic component is provided between the high temperature component and the supporting component. A device for supporting high temperature components in an aircraft engine, which is characterized by being interposed. 2. The combustor duct and support components are formed from a high nickel base alloy and the high temperature components are formed from silicon carbide or silicon nitride.
A support device for a high temperature component in an aircraft engine according to claim 1.