CN213775788U - Assembly for gas compressor performance test piece and gas compressor performance test piece - Google Patents

Abstract

The utility model relates to a subassembly and compressor performance test piece for compressor performance test piece. The assembly includes a main flow in-channel casing having at least a first surface and a lap end surface, wherein a first labyrinth feature is formed on the lap end surface of the main flow in-channel casing; the rear bearing case is at least provided with a second surface facing the first surface and a lapping end surface, wherein a second labyrinth feature is formed on the lapping end surface of the rear bearing case, the rear bearing case is provided with a sealing ring installation groove on the second surface, and the first labyrinth feature and the second labyrinth feature are meshed to enable the case to be lapped with the rear bearing case in the main runner; and the radial contact type sealing ring can be arranged in the sealing ring mounting groove and is attached to the first surface of the casing in the main flow channel.

Description

Assembly for gas compressor performance test piece and gas compressor performance test piece

Technical Field

The utility model relates to an aircraft engine field, more specifically relate to a compressor capability test spare that is used for subassembly of compressor capability test spare and contains this subassembly.

Background

At present, the performance test piece of the multistage axial flow compressor of the aeroengine at home and abroad needs the balance of the axial force of the rotor so that the thrust bearing of the test piece bears smaller axial force and ensures longer service life. However, due to the limitation of the equipment capacity of the test bed, a rotor axial force balancing system is generally required to be arranged in a compressor performance test piece. The rotor axial force balance system mainly comprises a balance cavity, a rotor balance disc is arranged on one side of the balance cavity, and high-pressure gas is injected into the balance cavity, so that the rotor balance disc obtains an axial force in the direction along with the airflow, and the rotor axial force in the direction opposite to the airflow flowing direction generated when the performance test piece of the gas compressor runs is balanced. The axial force balance system of the performance test piece of the multistage axial flow compressor has the following problems:

the balance cavity is generally positioned on the inner side of a main flow channel of an exhaust section of the test piece, the main flow channel of the exhaust section is composed of an outer casing and an inner casing, the outer casing is generally rigidly connected with a rear bearing machine casing of the test piece due to the requirement of transferring the load of the test piece, meanwhile, in order to avoid the situation that the outer casing and the inner casing are connected with the rear bearing machine casing over-constrained, the inner casing can only adopt a lap joint matching mode with the rear bearing machine casing, the air tightness at the lap joint position is poor, and high-temperature and high-pressure gas in the main flow channel inevitably leaks and flows into the inner side of the inner casing. Leaked high-temperature, high-pressure gas may enter peripheral cavities such as a test piece balance cavity, a rear bearing cavity and the like. For example, the temperature of the cavity in the rear bearing cavity is increased under the combined action of heat conduction and heat radiation, and the increase of the temperature of the cavity has the risk of coking or spontaneous combustion of lubricating oil in the bearing cavity, thereby seriously threatening the safe operation of a test piece.

Therefore, there is a need in the art for a new assembly sealing structure for a performance test piece of a compressor, which can effectively solve the problem that high-temperature and high-pressure gas outside an inner casing leaks to a low-pressure chamber inside the inner casing due to existence of a balance cavity in a performance test piece of a multistage axial flow compressor.

SUMMERY OF THE UTILITY MODEL

An object of the present invention is to provide a component for a compressor performance test piece, which can effectively reduce the amount of gas leaked from high temperature and high pressure gas on one side of an inner casing to the other side of the inner casing, and further ensure the safe operation of the multistage axial flow compressor performance test piece containing the component.

Specifically, an exemplary embodiment of the present invention provides an assembly for a compressor performance test piece, including: a main flow in-duct cartridge having at least a first surface and a lapping end surface, wherein a first labyrinth feature is formed on the lapping end surface of the main flow in-duct cartridge; a rear bearing case having at least a second surface facing the first surface and having a landing end face, wherein a second labyrinth feature is formed on the landing end face of the rear bearing case, the rear bearing case having a seal ring mounting groove on the second surface, wherein the first and second labyrinth features engage such that the main runner inner case lands on the rear bearing case; and the radial contact type sealing ring can be arranged in the sealing ring mounting groove and is attached to the first surface of the casing in the main flow channel. In this way, leakage of high-pressure gas from one side of the casing in the main flow channel into the low-pressure region on the other side via the overlap region can be prevented or effectively reduced.

Optionally, the first labyrinth feature includes a plurality of protrusions extending outwardly from the shiplap end face of the case within the main flowpath, and the second labyrinth feature includes a plurality of recesses recessed inwardly from the shiplap end face of the rear messenger case, wherein each protrusion of the plurality of protrusions is embedded in a corresponding recess of the plurality of recesses. In particular, a gap between a joint end face of the casing and a joint end face of the rear bearing casing in the main runner and gaps between the plurality of protrusions and the plurality of recesses form a labyrinth path for gas to flow.

Optionally, the radial contact seal ring is an annular seal ring having an opening and includes a first end and a second end, wherein in an unconstrained state, the first end and the second end of the radial contact seal ring have a gap therebetween, and upon installation of the radial contact seal ring in the seal ring installation groove and in engagement with the first surface, the first end and the second end of the radial contact seal ring are brought into proximity with one another such that the gap is reduced.

Optionally, the material of the radial contact seal ring is selected to have a greater coefficient of linear expansion than the material of the rear messenger case.

The exemplary embodiment of the utility model provides a compressor performance test piece still is provided, include: the assembly as described above, wherein the casing within the primary flowpath further has an outer surface opposite the first surface; an air intake space fluidly coupled to an outer surface of a casing within the primary flowpath; and a balancing cavity fluidly coupled to a first surface of a casing within the primary flowpath and fluidly coupled to a second surface of the rear bearing casing, the balancing cavity having a lower pressure than the intake space, wherein the assembly is capable of inhibiting gas in the intake space from leaking into the balancing cavity. In this way, safe operation of the compressor performance test piece is ensured.

Optionally, the compressor performance test piece further includes: the balance disc is arranged below the rear bearing case; the sealing disc is connected with the inner casing of the main flow channel; and the drum is arranged below the sealing disc and is rigidly connected with the balance disc, wherein the balance cavity is limited by the balance disc, the sealing disc, the drum, the casing in the main runner and the rear bearing box.

Optionally, the compressor performance test piece further includes: the main runner outer casing is rigidly connected with the rear bearing engine casing; and the diffuser part is rigidly connected with the outer casing of the main flow channel and the inner casing of the main flow channel, and the air inlet space is limited by the outer casing of the main flow channel, the diffuser part, the inner casing of the main flow channel and the rear bearing casing.

Drawings

The invention may be better understood by describing exemplary embodiments thereof in conjunction with the following drawings, in which:

fig. 1 shows a schematic cross-sectional view of an assembly for a compressor performance test piece according to an exemplary embodiment of the present invention.

Fig. 2 shows a front view of a seal ring according to a preferred embodiment of the present invention and an enlarged view of an opening portion of the seal ring; and

fig. 3 shows a schematic cross-sectional view of a compressor performance test piece according to an exemplary embodiment of the present invention.

Detailed Description

In the following description of the embodiments of the present invention, it is noted that in the detailed description of the embodiments, all the features of the actual embodiments may not be described in detail in order to make the description concise and concise. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which will vary from one implementation to another.

Unless otherwise defined, technical or scientific terms used in the claims and the specification should have the ordinary meaning as understood by those having ordinary skill in the art to which the present invention belongs. The use of "first," "second," and similar terms in the description and in the claims does not indicate any order, quantity, or importance, but rather is used to distinguish one element from another. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.

Fig. 1 shows a schematic cross-sectional view of an assembly for a compressor performance test piece according to an exemplary embodiment of the present invention. Referring to fig. 1, an assembly for a compressor performance test piece includes a main runner inner casing 10, a rear bearing casing 20, and a radial contact seal ring 30.

The main runner inner casing 10 may have at least a first surface 101 and a first overlap end surface 102. A first labyrinth feature may be formed on the first landing end face 102 of the casing 10 within the primary flowpath.

The rear messenger case 20 may have at least a second surface 201 facing the first surface 101 and a second overlapping end surface 202. A second labyrinth feature may be formed on the second lap end face 202 of the aft messenger case 20.

For example, a first labyrinth feature may include a plurality of protrusions 110 extending outwardly from the first landing end face 102 of the casing 10 within the primary flowpath, while a second labyrinth feature may include a plurality of recesses 210 recessed inwardly from the second landing end face 202 of the aft bearing casing 20. Each of the plurality of protrusions 110 may be embedded in a corresponding one of the plurality of recesses 210. As such, the gap between the first lap end surface 102 of the casing 10 and the second lap end surface 202 of the rear bearing casing 20 and the gaps between the plurality of protrusions 110 and the plurality of recesses 210 in the main runner may form a labyrinth path for the gas to flow, such that the gas experiences greater resistance through such a gas flow labyrinth path due to the "labyrinth effect" to substantially reduce the gas leakage flow at the lap location. Note that while only a non-limiting example of a labyrinth feature is described herein, one skilled in the art will appreciate that the first and second labyrinth features may also take a variety of different forms, so long as they are capable of forming a labyrinth path for gas flow when mated (e.g., engaged).

The rear messenger case 20 may have a gasket mounting groove 220 on the second surface 201. The first and second labyrinth features may engage such that the casing 10 overlaps the aft bearing casing 20 within the primary flowpath.

The radial contact seal ring 30 can be installed in the seal ring installation groove 220 and be fitted to the first surface 101 of the casing 10 in the main flow passage, thereby sealing between the first surface 101 and the second surface 201 to prevent or greatly reduce the flow of gas between the first surface 101 and the second surface 201.

The above describes in detail an assembly for a compressor performance test piece according to an exemplary embodiment of the present invention. The assembly provides a composite sealing structure, can be used for a performance test piece of a multistage axial flow compressor of an aircraft engine, and can prevent or effectively reduce the leakage of high-pressure gas on one side of a casing 10 in a main runner into an adjacent low-pressure chamber (such as a balance chamber) through a lap joint area.

Alternatively, referring to fig. 2, for ease of installation, the radial contact seal ring 30 may be an annular seal ring having an opening. The left side of fig. 2 shows a schematic front view of the seal ring 30, wherein openings are formed at the positions of the seal ring 30 as indicated by circles; the right side of fig. 2 shows an enlarged view of the locations indicated by the circles. As shown, the radial contact seal ring 30 may include a first end 301 and a second end 302. In the unconstrained state, the first end 301 and the second end 302 of the radial contact seal ring 30 have a gap of width L therebetween. When the radial contact type seal ring 30 is installed in the seal ring installation groove 220 described with respect to fig. 1 and is engaged with the first surface 101, the first end 301 and the second end 302 of the radial contact type seal ring 30 approach each other such that the interval is reduced. The design of the sealing ring can ensure that the sealing ring is easily compressed in the sealing groove during assembly, and after the assembly is completed, the sealing ring is radially and freely increased to be tightly attached to the inner casing of the main flow passage, so that the sealing effect is realized.

Alternatively, the material of the radial contact seal ring 30 may be selected to have a greater coefficient of linear expansion than the material of the aft bearing box 20. For example, the material of the radial contact seal ring 30 may be a material such as GH 4169.

The utility model also provides a compressor capability test spare.

Referring to fig. 3, a compressor performance test piece may include the components as described above, i.e., including the casing 10 in the main flow passage, the rear bearing casing 20, and the radial contact seal ring 30. The main flow channel inner casing 10 may also have an outer surface 103 opposite the first surface 101.

The compressor performance test piece can also comprise an air inlet space 1 and a balance cavity 2. The intake space 1 is fluidly coupled to the outer surface 103 of the casing 10 in the primary channel, while the balance chamber 2 is fluidly coupled to the first surface 101 of the casing 10 in the primary channel and to the second surface 201 of the rear bearing casing 20. The expression "chamber a is fluidly coupled to surface B" is intended to mean that a fluid (e.g., a gas) in chamber a is capable of contacting surface B and may be transferred along surface B. Ideally, the balance cavity 2 is fluidly coupled to only a portion of the first and second surfaces 101, 102, as the radial contact seal ring 30 provides a seal between the first and second surfaces 101, 102, thereby avoiding fluidly coupling the balance cavity 2 to the remainder of the first and second surfaces 101, 102 (e.g., the portion near the overlapping end faces). In use, high temperature, high pressure gas may enter the inlet space 1 via the gas flow passage such that the temperature and pressure in the inlet space 1 rise and exceed the internal temperature and pressure of the balancing chamber 2. The inlet space 1 is also fluidly coupled with the overlap end face and the labyrinth feature, but as mentioned above, due to the "labyrinth effect", the gas in the inlet space 1 experiences a greater resistance when passing through the labyrinth path thereby substantially reducing the amount of leakage of gas in the inlet space 1 at the overlap region 3. In this manner, the assembly described hereinabove is capable of suppressing the gas in the intake space 1 from leaking into the balance chamber 2.

The compressor performance test piece can further comprise a balance disc 40 arranged below the rear force bearing casing 20, a sealing disc 50 rigidly connected with the casing 10 in the main runner, and a drum 60 arranged below the sealing disc 50 and rigidly connected with the balance disc 40. The balance disk 40, the sealing disk 50, the drum 60, the main runner inner casing 10 and the rear bearing casing 20 jointly define a balance cavity 2.

The compressor performance test piece may further include a main flow channel outer casing 70 rigidly connected to the rear bearing casing 20, and a diffuser member 80 rigidly connected to both the main flow channel outer casing 70 and the main flow channel inner casing 10. The main channel outer casing 70, diffuser member 80, main channel inner casing 10 and aft bearing casing 20 collectively define an intake air space 1. A main flow passage is defined between the main flow passage outer casing 70 and the main flow passage inner casing 10. The gas flow passage formed in the diffuser member 80 may be a portion of the main flow passage. The high-temperature, high-pressure gas continues into the inlet space 1 via the primary flow channel (as indicated by the arrows in fig. 3), so that the inlet space 1 can have a higher pressure than the pressure in the balancing chamber 2.

If the air tightness of the lap joint position 3 between the casing 10 and the rear bearing box 20 in the main flow channel is poor, a large amount of high-temperature and high-pressure gas in the main flow channel leaks into a low-pressure chamber (for example, a balance chamber) on the inner side of the casing 10 in the main flow channel, the temperature of a chamber in a rear bearing chamber (not shown) is increased under the combined action of heat conduction and heat radiation, the increase of the temperature of the chamber has the risk of coking or spontaneous combustion of lubricating oil in the bearing chamber, and the safe operation of a test piece is seriously threatened.

However, in the above-described compressor performance test piece, since the labyrinth gas flow path is formed at the overlap position 3 between the casing 10 and the rear bearing casing 20 in the main flow passage, the resistance to which the gas is subjected when flowing therethrough is greatly increased, thereby greatly reducing the high-temperature, high-pressure gas flow leakage flow rate. In addition, in such a compressor performance test piece, the radial small clearance fit surfaces (i.e., the first surface 101 and the second surface 201) between the casing 10 and the rear bearing casing 20 in the main flow passage and the radial contact type seal ring 30 disposed therebetween are also designed to be simultaneously adhered to the casing and the rear bearing casing in the main flow passage, thereby achieving a sealing effect and greatly increasing the safety of the axial flow compressor performance test piece.

So far, it has been described that an assembly for a compressor performance test piece and a compressor performance test piece comprising such an assembly according to the present invention. The embodiment of the utility model provides a compound structure of obturating of balanced chamber stator section for balanced chamber stator overlap joint section of multistage axial compressor performance test piece of aeroengine mainly comprises the terminal surface labyrinth section of obturating and the radial contact sealing washer section of obturating of arranging at sprue high temperature, high-pressure gas leakage path (balanced chamber stator overlap joint section passageway promptly). The labyrinth sealing section of the end surface is formed by matching a labyrinth section arranged on the end surface of the casing in the main flow passage with a labyrinth section arranged on the corresponding end surface of the rear bearing casing. The labyrinth seal section of the end face ensures the assembly feasibility between the casing and the rear bearing machine casing in the main runner, and simultaneously, labyrinth seal is applied to the sealing of the stator overlap section of the balance cavity, high-temperature and high-pressure airflow generates resistance when passing through the labyrinth seal structure of the end face due to the labyrinth effect, so that the leakage flow is greatly reduced, the sealing purpose is realized, and the sealing effect is enhanced along with the increase of the number of layers of the labyrinth. The radial contact type sealing ring sealing section is arranged at the joint surface of the main runner inner casing and the rear bearing machine casing in the lap joint radial small gap, the radial contact type sealing ring is arranged in a sealing ring mounting groove on the rear bearing machine casing, an open type is adopted, a micro interval is arranged in a free state, compression in a sealing groove is ensured during assembly, radial free increase is achieved after assembly is completed until the radial contact type sealing ring is tightly attached to the main runner inner casing, and then the sealing effect is achieved. The radial contact type sealing ring sealing section can also select the contact type sealing ring to be made of a material with a linear expansion coefficient different from that of the casing in the main runner and the rear bearing machine casing, and the larger linear expansion coefficient enables the contact type sealing ring to be further tightly attached to the casing in the main runner under the action of high temperature, so that the sealing effect is better enhanced. The end surface labyrinth sealing section and the radial contact type sealing ring sealing section are combined for use, so that the sealing effect of the stator overlapping section of the balance cavity of the performance test piece of the multistage axial flow compressor is greatly improved, and the leakage amount of high-temperature and high-pressure gas in the main flow passage is reduced.

Although the present invention has been described with reference to the present specific embodiments, it will be understood by those skilled in the art that the above embodiments are merely illustrative of the present invention, and various equivalent changes and substitutions may be made without departing from the spirit of the present invention, and therefore, changes and modifications to the above embodiments within the spirit of the present invention will fall within the scope of the claims of the present application.

Claims (8)

1. An assembly for a compressor performance test piece, comprising:

a main flow in-duct cartridge having at least a first surface and a lapping end surface, wherein a first labyrinth feature is formed on the lapping end surface of the main flow in-duct cartridge;

a rear bearing case having at least a second surface facing the first surface and having a landing end face, wherein a second labyrinth feature is formed on the landing end face of the rear bearing case, the rear bearing case having a seal ring mounting groove on the second surface, wherein the first and second labyrinth features engage such that the main runner inner case lands on the rear bearing case; and

a radial contact seal ring mountable in the seal ring mounting groove and conforming to the first surface of a casing in the primary flowpath.

2. The assembly of claim 1, wherein the first labyrinth feature includes a plurality of protrusions extending outwardly from a shiplap end surface of a casing within the primary flowpath, and the second labyrinth feature includes a plurality of recesses recessed inwardly from a shiplap end surface of the aft messenger casing, wherein each protrusion of the plurality of protrusions is embedded in a corresponding recess of the plurality of recesses.

3. The assembly of claim 2, wherein a gap between a landing end face of a casing and a landing end face of the rear messenger casing in the main flow passage and a gap between the plurality of projections and the plurality of recesses form a labyrinth path for gas flow.

4. The assembly of claim 1, wherein the radial contact seal ring is an annular seal ring having an opening and includes a first end and a second end, wherein in an unconstrained state, the first end and the second end of the radial contact seal ring have a spacing therebetween, and upon installation of the radial contact seal ring in the seal ring installation groove and in engagement with the first surface, the first end and the second end of the radial contact seal ring are brought into proximity with one another such that the spacing is reduced.

5. The assembly of claim 1, wherein the material of the radial contact seal ring is selected to have a greater coefficient of linear expansion than the material of the aft messenger case.

6. A compressor performance test piece, comprising:

the assembly of claims 1-5, wherein the main flow channel inner casing further has an outer surface opposite the first surface;

an air intake space fluidly coupled to an outer surface of a casing within the primary flowpath; and

a balancing chamber fluidly coupled with a first surface of a case within the primary flowpath and fluidly coupled with a second surface of the rear bearing case, the balancing chamber having a lower pressure than the intake space,

wherein the assembly is capable of inhibiting gas in the intake space from leaking into the balance chamber.

7. The compressor performance test piece of claim 6, further comprising:

the balance disc is arranged below the rear bearing case;

the sealing disc is connected with the inner casing of the main flow channel; and

a drum disposed below the obturating disc and rigidly connected to the balancing disc,

wherein the balance cavity is defined by the balance disc, the sealing disc, the drum, the casing in the main runner and the rear bearing casing.

8. The compressor performance test piece of claim 7, further comprising:

the main runner outer casing is rigidly connected with the rear bearing engine casing; and

a diffuser component, the diffuser component is rigidly connected with the outer casing of the main flow channel and the inner casing of the main flow channel,

wherein the air intake space is defined by the main flow channel outer casing, the diffuser member, the main flow channel inner casing, and the rear bearing casing.

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