KR20160139408A - Compressors with casing treatments in gas turbine engines - Google Patents

Compressors with casing treatments in gas turbine engines Download PDF

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Publication number
KR20160139408A
KR20160139408A KR1020150074096A KR20150074096A KR20160139408A KR 20160139408 A KR20160139408 A KR 20160139408A KR 1020150074096 A KR1020150074096 A KR 1020150074096A KR 20150074096 A KR20150074096 A KR 20150074096A KR 20160139408 A KR20160139408 A KR 20160139408A
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KR
South Korea
Prior art keywords
ring
casing
compressor
gas turbine
groove
Prior art date
Application number
KR1020150074096A
Other languages
Korean (ko)
Inventor
김형윤
Original Assignee
두산중공업 주식회사
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Publication date
Application filed by 두산중공업 주식회사 filed Critical 두산중공업 주식회사
Priority to KR1020150074096A priority Critical patent/KR20160139408A/en
Publication of KR20160139408A publication Critical patent/KR20160139408A/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present invention relates to a cylindrical groove ring installed in a gas turbine compressor casing, comprising: at least one ring-shaped groove formed on an inner surface of the ring, wherein an outer surface of the ring comes in contact with the casing; and a spring which connects the casing and one side surface of the ring to compress and stretch the ring toward a gas turbine rotary shaft. According to the present invention, in a starting operation section of a compressor, driving stability may be secured by minimizing vibration and impact because a stall margin and a surge margin are secured by a groove of the casing in accordance with a conventional technology. In addition, when the compressor enters a normal operation section, pressure in the compressor is increased, and compressed air caused thereby pushes the spring, so the casing groove is closed. As a result, a decrease in efficiency of the compressor is minimized, so efficiency in the normal operation section may be improved.

Description

Technical Field [0001] The present invention relates to a gas turbine compressor having casing treatment,

The present invention relates to a compressor of a gas turbine, and more particularly to a casing groove of a gas turbine compressor.

A gas turbine is a rotary type heat engine that drives a turbine with high-temperature, high-pressure combustion gas. Generally, it consists of compressor, combustor and turbine. Since the compressor produces severe vibration due to stall and surge in the low flow area, it causes not only a deterioration in performance such as efficiency but also a problem in operation stability of the compressor. Therefore, It should be designed.

Conventionally, when the grooves are formed on the case surface of the compressor to form the casing groove, the stall phenomenon caused by the interaction of the tip leakage vortex and the shock wave generated in the vicinity of the case of the compressor is delayed to improve the stall margin, It is known that it can be increased.

However, the method of forming grooves in the casing is effective in the starting section, but there is a problem in that the efficiency of the compressor is lowered in the normal operating section in which the flow rate is increased.

Korean Patent Publication No. 10-2013-0074012

The present invention not only improves the operational safety of the start section by using the spring and the casing groove but also improves the compressor efficiency even in the normal operation section.

According to an aspect of the present invention, there is provided a gas turbine compressor casing, comprising: a cylindrical ring disposed inside a gas turbine compressor casing, the ring outer surface being in contact with the casing and having at least one annular groove And a spring ring connecting the one side of the ring and the casing to allow the ring to be compressed and tensioned in the direction of the axis of rotation of the gas turbine.

According to an embodiment of the present invention, the outer surface of the ring and the inner surface of the casing, which is in contact with the outer surface, may be formed in parallel with the rotation axis of the gas turbine compressor.

According to an embodiment of the present invention, the shape of the side surface of the ring, to which the spring is not connected, may be a groove ring characterized in that the inner circle of the ring gradually widens and meets the outer circle of the ring.

According to one embodiment of the present invention, the groove ring may be a groove ring which further includes at least one wedge protruding from the outer surface of the ring and formed parallel to the rotational axis direction of the ring.

According to an embodiment of the present invention, there is provided a gas turbine compressor including a blade and a casing, the compressor having a cylindrical shape, a cylindrical gas turbine compressor installed inside the casing and surrounding a circular locus due to rotation of the blade, One or more annular grooves formed on the inner surface of the ring and formed along the ring and one side of the ring and the inner surface of the casing so as to compress and compress the ring in the direction of the axis of rotation of the gas turbine, The inner surface of the casing contacting the outer surface of the ring may be a gas turbine compressor formed in parallel with the axis of rotation of the gas turbine compressor.

According to an embodiment of the present invention, the gas turbine compressor further includes at least one wedge protruding from the outer surface of the ring and formed parallel to the rotation axis direction of the ring, wherein the casing is provided with a groove engaging with the wedge, Lt; / RTI >

According to an embodiment of the present invention, there is provided a method of controlling an operation of a gas turbine compressor,

A ring which is in the shape of a cylinder and which is in contact with the inner surface of the compressor casing and which is parallel to the compressor rotation axis, one or more annular grooves formed on the inner surface of the ring and one side surface of the ring and the inner surface of the casing, And a spring for compressing and tensioning the gas turbine in the direction of the axis of rotation of the gas turbine,

Wherein the spring is not compressed when the compressor is in a starting operation section and the spring is compressed when the compressor is in a normal operation section and the grooves of the ring do not wrap the rotating surface of the compressor, So as to surround the rotating surface of the compressor blade.

According to the present invention, the stall margin and the surge margin are secured by the grooves of the casing according to the prior art in the start-up operation period of the compressor, so that the vibration and shock are minimized and the operation stability can be ensured.

In addition, when the compressor enters the normal operation section, the pressure in the compressor rises and the compressed air pushes the spring to close the casing groove. As a result, it is possible to minimize the decrease in the compressor efficiency and increase the efficiency in the normal operation period.

1 shows a groove of a compressor casing according to the prior art.
2 shows a compressor casing according to an embodiment of the present invention.
3 illustrates a side view of a groove ring according to an embodiment of the present invention.
4 illustrates a groove ring and a corresponding casing according to an embodiment of the present invention.

Hereinafter, some embodiments of the present invention will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the difference that the embodiments of the present invention are not conclusive.

In describing the components of the embodiment of the present invention, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected," "coupled," or "connected. &Quot;

1 shows a groove of a compressor casing according to a conventional technique. It is possible to improve the stall margin by delaying the stall phenomenon caused by the interaction between the tip leakage vortex and the shock wave generated near the casing of the compressor by forming grooves on the inner surface of the casing adjacent to the compressor blades and forming the casing grooves, It is known that it is possible to increase.

The grooves formed in the casing are effective when the flow is small, but the efficiency of the compressor is hindered as the flow increases. Therefore, the method of forming the grooves in the casing is effective in the start section, but has a problem that the efficiency of the compressor is lowered in the normal operation section where the flow rate is increased.

2 shows a compressor casing 200 according to an embodiment of the present invention. Fig. 2 (a) shows the case when the flow is small, and (b) shows when the flow is large. The groove ring 300 has a circular shape along the casing 200 so as to be adjacent to the rotation surface of the blade 100 and has at least one groove formed on the inner surface thereof. The number of grooves is not limited and may be suitably adjusted as needed. A spring 400 is connected to one side of the groove ring 300 and the other side of the spring 400 is connected to the casing 200. As the spring 400 is tensioned and contracted, the position of the groove ring 300 is moved together. The outer surface of the groove ring 300 (the surface opposite to the inner surface on which the grooves are formed) remains in contact with the inner surface of the casing 200 and moves along the spring 400. The spring 400 means all elastic bodies that can be contracted and tensioned, and various forms are possible.

According to the present invention, since the groove ring 300 is moved horizontally to the left and to the right, the rotating surface of the blade 100 and the inner surface of the groove ring 300 are not parallel to the axis of rotation of the compressor, And the inner surface of the casing 200, which is in contact with the groove ring 300, are both formed and arranged in parallel with the rotation axis of the compressor.

Referring to FIG. 2, a ring installed in the gas turbine compressor casing 200, the outer surface of which is in contact with the casing 200, and has at least one annular groove formed on the inner surface of the ring, A groove ring 300 including a spring 400 connecting the casing 200 to compress and tension the ring in the direction of the axis of rotation of the gas turbine can be implemented.

According to the present invention, the groove ring 300 is positioned in a state where the spring 400 is not compressed in the start-up operation period of the compressor. Referring to FIG. 2 (a), the stall margin and the surge margin are secured by the grooves of the casing 200 as in the conventional technique, so that vibration and impact are minimized, and the operation stability can be ensured.

Also, when the compressor enters the normal operation period, the pressure in the compressor rises and the compressed air pushes out the groove ring 300, thereby causing the spring 400 to compress. Referring to FIG. 2 (b), as the flow increases and the pressure inside the compressor rises, the groove ring 300 moves to close the groove. As a result, it is possible to minimize the decrease in the compressor efficiency and increase the efficiency in the normal operation period.

According to one embodiment of the present invention, referring to FIG. 2, a ring-shaped ring provided inside the gas turbine compressor casing 200, the outer surface of the ring is in contact with the casing 200, And a spring (400) that connects the casing (200) to the annular groove and the one side of the ring to compress and tension the ring in the direction of the axis of rotation of the gas turbine.

According to an embodiment of the present invention, the outer surface of the ring and the inner surface of the casing 200, which is in contact with the outer surface, are formed parallel to the rotation axis of the gas turbine compressor. Lt; / RTI >

2 is a gas turbine compressor including a blade 100 and a casing 200. The gas turbine compressor has a cylindrical shape and is disposed in contact with an inner surface of the casing 200, One or more annular grooves formed on the inner surface of the ring and formed along the ring, and one side surface of the ring and the inner surface of the casing (200) And a spring (400) for connecting the ring to compress and tension the ring in the direction of the axis of rotation of the gas turbine, wherein the inner surface of the casing (200), which contacts the outer surface of the ring, And may be a gas turbine compressor formed in parallel.

Fig. 3 shows a modification of the side surface of the groove ring 300. As shown in Fig. One side of the groove ring 300 is connected to the spring 400, and the other side is a portion receiving pressure from the compressed air. Since the pressure side is the part that is directly subjected to the gas flow, it can be transformed into an efficient form to receive the force. Three examples are shown in FIG. 3, but the present invention is not limited thereto and various applications are possible. 3 (a) shows a shape in which the inner surface of the groove ring 300 is in contact with the outer surface while drawing a curve. Fig. 3 (b) shows a shape similar to the shape shown in Fig. The spring 400 is connected to one side of the recessed portion. (c), the inner surface of the groove ring 300 does not draw a curved line, but forms a stepped shape of a straight line, and is in contact with the outer surface of the groove ring 300.

According to an embodiment of the present invention referring to FIG. 3, the shape of the side surface of the side surface of the ring, to which the spring 400 is not connected, is characterized in that the inner circle of the ring is gradually widened to meet with the outer circle of the ring The groove ring 300 may be a groove ring.

Referring to FIG. 4, a modification of the groove ring 300 and a corresponding casing 200 are shown. 4 (a) to 4 (d) show a portion protruding from the outer surface of the groove ring 300 and a casing 200 in which an inner surface is engaged with the protruding portion. (a), a wedge having an inverted triangular shape protrudes from the outer surface of the groove ring 300, (b) has a T-shaped protrusion, and (c) and (d) A projection is formed. There may be one or more wedges or protrusions formed on the outer surface of the groove ring 300, and a plurality of wedges or protrusions may be formed. In FIG. 4, two wedges or protrusions are shown protruding, but this is only one example, and the shape of the wedge or protrusion is not limited to the four types shown in the drawings.

When the blade 100 of the compressor rotates, the groove ring 300 that surrounds the blade 100 may rotate together. When the groove ring 300 is rotated, a problem may occur in the spring 400 that connects the groove ring 300 to the casing 200, and the efficiency of the compressor may be reduced. 4, when the wedge or the protruded groove ring is coupled with the casing 200, the groove ring 300 is fixed so as not to rotate, and the groove ring 300 is fixed to the spring 400 It is possible to move in the axial direction according to tension and compression, thereby enabling efficient control.

According to an embodiment of the present invention, referring to FIG. 4, the groove ring 300 may further include at least one wedge protruding from the outer surface of the ring and formed parallel to the rotation axis direction of the ring.

A method of controlling operation of a gas turbine compressor according to an embodiment of the present invention includes the steps of forming a ring in a cylindrical shape and in contact with the inner surface of the compressor casing 200 and parallel to the compressor rotation axis, And a spring (400) connecting one side of the ring and the inner surface of the casing (200) to compress and tension the ring in the direction of the axis of rotation of the gas turbine A stop or start step in which the spring 400 is not compressed when the compressor is in the starting operation period and the groove of the ring does not wrap the rotating surface of the compressor blade 100 and when the compressor is in the normal operation section, 400 may be compressed so that the groove of the ring encloses the rotating surface of the compressor blade 100.

While the present invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiments. That is, within the scope of the present invention, all of the components may be selectively coupled to one or more of them. Furthermore, the terms "comprises", "comprising", or "having" described above mean that a component can be implanted unless otherwise specifically stated, But should be construed as including other elements. All terms, including technical and scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. Commonly used terms, such as predefined terms, should be interpreted to be consistent with the contextual meanings of the related art, and are not to be construed as ideal or overly formal, unless expressly defined to the contrary.

The foregoing description is merely illustrative of the technical idea of the present invention, and various changes and modifications may be made by those skilled in the art without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

100: blade
200: casing
300: Groove ring
400: spring

Claims (7)

1. A ring of a cylindrical shape provided inside a gas turbine compressor casing,
The ring outer surface being in contact with the casing and having at least one annular groove formed in the inner surface of the ring;
A spring connecting the one side of the ring and the casing to compress and tension the ring in the direction of the axis of rotation of the gas turbine;
≪ / RTI >
The method according to claim 1,
The outer surface of the ring and the inner surface of the casing, which is in contact with the outer surface,
Wherein the groove ring is formed parallel to the rotation axis of the gas turbine compressor.
3. The method of claim 2,
The shape of the side of the ring, to which the spring is not connected,
And the inner circle of the ring gradually widens to meet the outer circle of the ring.
4. The method according to claim 2 or 3,
Further comprising at least one wedge protruding from the outer surface of the ring and formed parallel to the rotational axis direction of the ring.
A gas turbine compressor comprising a blade and a casing,
A ring disposed in a cylindrical shape in close contact with an inner surface of the casing and surrounding a circular locus caused by the rotation of the blade, the ring being parallel to the rotation axis of the gas turbine compressor;
One or more annular grooves formed on the inner surface of the ring and formed along the ring;
A spring connecting one side of the ring and the inner surface of the casing to compress and tension the ring in the direction of the axis of rotation of the gas turbine;
Wherein the inner surface of the casing, which abuts the outer surface of the ring, is formed parallel to the axis of rotation of the gas turbine compressor.
6. The method of claim 5,
Further comprising at least one wedge protruding from the outer surface of the ring and formed parallel to the rotation axis direction of the ring, wherein the casing is formed with a groove engaging with the wedge.
A method of controlling an operation of a gas turbine compressor,
A ring which is in the shape of a cylinder and which is in contact with the inner surface of the compressor casing and parallel to the compressor rotation axis, one or more annular grooves formed on the inner surface of the ring and one side surface of the ring and the inner surface of the casing, And a spring for compressing and tensioning the gas turbine in the direction of the axis of rotation of the gas turbine,
A stopping or starting step in which the spring is not compressed when the compressor is in the starting operation section and the groove of the ring does not wrap the rotating surface of the compressor blade;
A normal step of compressing the spring when the compressor is in a normal operation period so that the groove of the ring surrounds the rotating surface of the compressor blade;
And a control unit for controlling the operation of the gas turbine compressor.
KR1020150074096A 2015-05-27 2015-05-27 Compressors with casing treatments in gas turbine engines KR20160139408A (en)

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KR1020150074096A KR20160139408A (en) 2015-05-27 2015-05-27 Compressors with casing treatments in gas turbine engines

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113883095A (en) * 2021-11-02 2022-01-04 北京航空航天大学 Casing and fluid power equipment

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20130074012A (en) 2011-12-26 2013-07-04 한국항공우주연구원 Heating apparatus of gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20130074012A (en) 2011-12-26 2013-07-04 한국항공우주연구원 Heating apparatus of gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113883095A (en) * 2021-11-02 2022-01-04 北京航空航天大学 Casing and fluid power equipment

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