CN213655190U

CN213655190U - Impeller mechanical sealing assembly, low-pressure compressor and gas turbine

Info

Publication number: CN213655190U
Application number: CN202022303995.2U
Authority: CN
Inventors: 蔡宇桐; 林见南; 曾瑞慧
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-10-15
Filing date: 2020-10-15
Publication date: 2021-07-09
Anticipated expiration: 2030-10-15

Abstract

An object of the utility model is to provide an impeller machinery subassembly of obturating, it can solve the problem of at least one aspect that exists among the prior art. The utility model also provides a low pressure compressor and a gas turbine. To achieve the foregoing object, a turbomachinery sealing assembly for a low-pressure compressor including stator blades and a booster stage drum, comprises: the coating part is arranged on the stator blade and provided with at least one sealing part protruding towards the drum barrel of the pressure increasing stage, a gap allowing air flow circulation is formed between the sealing part and the periphery of the drum barrel of the pressure increasing stage, and no labyrinth is arranged on the drum barrel of the pressure increasing stage.

Description

Impeller mechanical sealing assembly, low-pressure compressor and gas turbine

Technical Field

The utility model relates to an impeller machinery subassembly, low pressure compressor and gas turbine of obturating.

Background

An axial flow type impeller mechanical compressor, which is a typical case of an axial flow aircraft engine, is composed of a low-pressure compressor (fan booster stage) and a high-pressure compressor, wherein the low-pressure compressor comprises an inlet fan, a booster stage and an intermediate unit body. The booster stage is used for improving the pneumatic performance of the front fan and the high-pressure compressor and increasing the pressure at the inlet of the high-pressure compressor. Because the air current is behind each level of pressure boost level blade, pressure increase, if not increase the structure of obturating at the position that stator blade lower extreme and rotor are connected, can lead to the air current refluence to leak, seriously influence the pressure boost of inner flow way gas, influence engine stability. The commonly used sealing form at present is the labyrinth sealing, the adopted coating is silicon resin containing hollow glass beads, and under the normal working condition, the coating and the labyrinth have a small gap configuration, so that a better sealing effect can be realized.

Fig. 1 shows a schematic view of an embodiment of a prior sealing structure, wherein the configuration of the coating under the prior pressurizing stage stator ring is shown as follows: the thick silicone coating 93 is matched with the comb teeth 92 on the drum barrel to form a matching mode of small gaps, so that the sealing effect is achieved. The number of the labyrinth 92 is generally two as shown in the figure, which is a cross-sectional view of a section of a prior sealing structure, and the coating 93 is a one-piece annular member. During the rotation of the rotor 91, the airflow passes through the stator blades 96, the rear side pressure is larger than the front side pressure, the airflow can flow from the front to the rear between the grid tooth 92 and the coating 93, and a small gap is formed between the grid tooth 92 and the coating 93 so as to effectively reduce the pressure of the airflow and play a role in sealing.

In the sealing structure shown in fig. 1, in order to ensure the sealing effect, the clearance between the labyrinth and the coating is small. To achieve smaller clearances, it is often necessary to increase the casing diameter within the boost stage or thicken the coating, both of which add significant weight to the engine. The processing difficulty is increased by processing the grid teeth on the drum. Meanwhile, the grate and the drum are integrally processed, and when the grate is damaged, the whole drum can be scrapped. Therefore, it is desirable to provide a sealing structure, which can reduce the weight and processing difficulty of the drum and improve the maintainability of the drum on the premise of ensuring the sealing effect.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an impeller machinery subassembly of obturating, it can solve the problem of at least one aspect that exists among the prior art.

Another object of the present invention is to provide a low pressure compressor, which includes the aforesaid sealing assembly for impeller machine.

It is a further object of the present invention to provide a gas turbine including the aforementioned low pressure compressor.

To achieve the foregoing object, a turbomachinery sealing assembly for a low-pressure compressor including a stator blade and a booster stage drum, comprises:

the coating piece is arranged on the stator blade and provided with at least one sealing part protruding towards the booster stage drum barrel, a gap allowing air flow to circulate is formed between the sealing part and the periphery of the booster stage drum barrel, and no labyrinth is arranged on the booster stage drum barrel.

In one or more embodiments, the obturating part is in a shape of a comb.

In one or more embodiments, two sealing parts are arranged on the coating member along the flowing direction of the airflow.

In one or more embodiments, the coating member is made of silicone.

In one or more embodiments, at least one notch portion is formed in the coating member.

To achieve another of the above objects, a low-pressure compressor comprises a stator blade and a booster stage drum, characterized in that an impeller mechanical seal assembly as described above is provided between the stator blade and the booster stage drum.

In one or more embodiments, the stator blade has a receiving portion therein, and the coating member is disposed in the receiving portion.

In one or more embodiments, the booster stage stator case in the low pressure compressor is a split case structure.

In one or more embodiments, the booster stage stator case in the low pressure compressor is assembled from a plurality of segments.

A gas turbine engine for achieving the aforementioned further object comprises a low-pressure compressor as described above.

The utility model discloses an advance effect includes following one or combination:

1) the sealing part is arranged on the coating part in the stator blade, so that a labyrinth structure on the booster stage drum barrel can be omitted on the premise of ensuring the sealing effect, and the weight of the coating part is about half of that of a labyrinth for objects with the same volume, so that the sealing part can play a role in reducing the weight.

2) When the sealing structure is abraded after the engine is in service, the coating can be reprocessed after the coating is coated, so as to recover the initial labyrinth gap, and compared with the maintenance of the labyrinth structure, the cost is lower and the maintainability is higher.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a schematic diagram of one embodiment of a prior art seal arrangement;

FIG. 2 shows a schematic cross-sectional view of one embodiment of the present turbomachinery seal assembly;

FIG. 3 is a schematic diagram of one embodiment of the present turbomachinery seal assembly as applied to a low pressure compressor.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.

It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.

It should be noted that the reference numerals described later and the reference numerals in the background art use different labeling systems, and there is no correlation between the reference numerals.

One or more of the terms herein are to be interpreted as follows:

turbo machinery (turbo machine): a power machine using continuous rotating blades as main body to convert the energy between fluid working medium and shaft power.

Grate (labyrinth): a non-contact sealing structure is mainly used for reducing backflow loss between stages of a gas compressor and is composed of a plurality of cavities formed by grid teeth.

Sealing coating (sealing coating): the coating is placed above the labyrinth and is not contacted with the labyrinth under normal conditions, the radial clearance of the labyrinth is reduced to realize the sealing effect of the labyrinth, and the labyrinth and the coating are allowed to be scraped and ground under abnormal conditions, so that the hardness and the weight of the coating are generally smaller than those of a labyrinth base body.

Silicone resin (silicone): a thermosetting polysiloxane polymer with a highly cross-linked structure has the dual characteristics of organic resin and inorganic materials, and has good electrical insulation property, temperature resistance and water resistance.

In order to solve the problem of one or more aspects existing in the existing sealing structure, an aspect of the present invention provides an impeller mechanical sealing assembly for a low pressure compressor, and fig. 2 shows a schematic sectional view of an embodiment of the present impeller mechanical sealing assembly. This impeller machinery seals subassembly and sets up between stator blade 2 and booster stage drum barrel 3 of low pressure compressor, and it includes: a coating element 1 arranged on the stator blade 2, the coating element 1 being provided with at least one seal 11 projecting towards the drum 3 of the pressure stage. It is to be understood that fig. 2 is a schematic view of a cross section of a low-pressure compressor, wherein the coating member 1 may actually be a rotating member, and the sealing portion 11 is a raised annular protrusion structure disposed on one side of an inner annular surface of the coating member 1.

Wherein the seals 11 are gaps 10 with the periphery of the pressure stage drum 3 that allow air flow between the seals, which may be in the direction of the arrows 4 shown in the figure. Due to the arrangement in the coating 1 of the stator blades 2, no prior art grate structure as shown in fig. 1 is provided on the booster stage drum 3.

In the mechanical seal assembly of the impeller, the seal part 11 is arranged on the coating part 1 in the stator blade, on the premise of ensuring the seal effect, the labyrinth structure on the booster stage drum barrel 3 can be omitted, and as for objects with the same volume, the weight of the coating part 1 is about half of the labyrinth, the arrangement can play a role in reducing the weight.

Meanwhile, when the sealing structure is abraded after the engine is in service, the coating can be reprocessed after the layer piece 1 is sprayed, so that the initial labyrinth gap is recovered, and the cost is lower and the maintainability is higher compared with the maintenance of the labyrinth structure.

While one embodiment of the present turbomachinery seal assembly is described above, in other embodiments of the present turbomachinery seal assembly, the present turbomachinery seal assembly may have more details, and at least some of the details may vary widely, in many respects from the embodiments described above. At least some of these details and variations are described below in several embodiments.

In one embodiment of the mechanical seal assembly of the impeller, the seal 11 is in the shape of a comb as shown in fig. 2, it is understood that, as mentioned above, the comb-shaped structure is only one of the cross-sectional structures shown in the drawings, and the actual structure of the comb shape can be understood as an annular comb-shaped structure which is convex along the inner annular surface and is easy to machine. In other embodiments different from those shown, the shape of the sealing part 11 may have other suitable modifications or changes, but is not limited thereto. As in one embodiment, the outer shape of the seal 11 may be a convex ring structure with a rectangular cross section.

In one embodiment of the turbomachinery sealing assembly, two seals 11 are provided on the coating member 1 in the flow direction of the gas flow 4 as shown in the figure. The two sealing parts 11 are arranged, so that the sealing effect of the sealing component can be guaranteed on the premise of not additionally increasing the total weight of the engine. In other embodiments different from those shown, the number of the sealing parts 11 may be changed as appropriate, but not limited thereto. As in one embodiment, the number of the sealing portions 11 may be three or more, wherein the number may be set according to the sealing effect and the weight to be obtained for different engines.

In one embodiment of the mechanical seal assembly of the impeller, the coating member 1 is made of silicone. Because the silicone resin is a thermosetting polysiloxane polymer with a highly cross-linked structure, the silicone resin has the dual characteristics of organic resin and inorganic materials, and has good electrical insulation property, temperature resistance and waterproof performance. Meanwhile, under the same volume, the silicon resin has lighter weight compared with the traditional grate structure. Preferably, the coating member 1 is made of silicone resin containing hollow glass beads.

In an embodiment of the mechanical seal assembly of the impeller, at least one notch (not shown in the figure) may be further formed in the coating member 1, and the notch may be formed in a circle along the inner ring of the coating member 1, or may be formed in a plurality of notches formed at intervals in the circumferential direction of the inner ring. By providing the notch portion, the weight of the coating material 1 can be further reduced, and the total weight of the engine can be reduced.

The turbomachinery sealing assembly as in one or more of the preceding embodiments may be used in a low pressure compressor, as shown in fig. 3, comprising stator blades 2 and a booster stage drum 3. The fan also comprises a fan disc 51, fan blades 52, an intermediate casing 53, a turbine shaft 54, a fan shaft 55 and the like. Wherein the turbomachinery sealing assembly as in one or more of the previous embodiments is disposed between the stator blades 2 and the booster stage drum 3.

In one embodiment of the low-pressure compressor, as shown in fig. 2, the stator blade 2 has a receiving portion 20 at one end, and the coating member 1 is disposed in the receiving portion 20.

In one embodiment of the low-pressure compressor, the booster stage stator casing in the low-pressure compressor is of a split casing structure, and in another embodiment, the booster stage stator casing in the low-pressure compressor is assembled by a plurality of fan-shaped sections, so that the assembly is more convenient, and the coating member 1 is more convenient to replace or repair.

The low-pressure compressor as in one or more of the preceding embodiments may be used in a gas turbine, such as an aircraft engine.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. A turbomachinery seal assembly for a low pressure compressor comprising stator blades and a booster stage drum, comprising:

2. The turbomachinery seal assembly of claim 1, wherein the seal is in the form of a labyrinth.

3. The turbomachinery seal assembly of claim 1, wherein two said seals are provided on said coating member in the direction of flow of the gas stream.

4. The turbomachinery seal assembly of claim 1 wherein said coating member is made of silicone.

5. The turbomachinery seal assembly of claim 1 wherein said coating member has at least one notch formed therein.

6. A low pressure compressor comprising a stator blade and a booster stage drum, wherein a turbomachinery seal assembly as recited in any of claims 1 to 5 is disposed between the stator blade and the booster stage drum.

7. The low pressure compressor as claimed in claim 6, wherein the stator vane has a receptacle therein in which the coating is disposed.

8. The low-pressure compressor as claimed in claim 6, wherein the stator casing of the booster stage in the low-pressure compressor is of a split casing construction.

9. The low-pressure compressor as claimed in claim 6, characterized in that the stator casing of the booster stage in the low-pressure compressor is assembled from a plurality of segments.

10. A gas turbine engine comprising a low-pressure compressor as claimed in any one of claims 6 to 9.