JP2012530870A - Annular flow path for turbomachinery - Google Patents

Abstract

  The present invention relates to a plurality of guide vanes (10) continuously arranged in the circumferential direction, the blade roots, the platform (16), and the blades (14) projecting radially toward the inside of the flow path (26). To an annular channel section (12) for a turbomachine having a guide vane (10) comprising: In the present invention, the boundary of the flow path (26) is formed by a shield element (22) on the platform side, and each shield element (22) is disposed between two directly adjacent wings (14). The shield element (22) is disposed above the platform (16) in a state where a gap is formed, and a collision cooling hole (24) is formed in the flow path section ( 12).

Description

  The present invention relates to a stator blade ring having a large number of stator blades continuously arranged in the circumferential direction, the blade root portion, the platform, and the blade blade projecting radially toward the inside of the flow path. An annular flow passage section for a turbomachine having a stator blade ring with a flow passage boundary between two directly adjacent blade blades on the platform side It relates to an annular channel section formed by a shield element that is arranged.

  For example, U.S. Patent No. 6,057,051 discloses an annular channel section referred to in the introduction. Specifically, the published patent specification discloses an axial flow type fluid machine when the platform is provided at a radially outer (root side) end and a radially inner (tip side) end of a blade blade. A stator blade ring having a blade blade curved in consideration of aerodynamics is disclosed. When the platform is installed on the turbine, it is covered with a ceramic heat shield. The heat shield is designed to cover the platform halves of two stator blades that are directly adjacent to each other in each set of heat shields. Accordingly, the heat shield member basically extends from the suction side wall of the blade blade of the first stator blade to the pressure side wall of the blade blade of the second stator blade. In this case, the ceramic heat shield member is fixedly connected to the blades of the gas turbine via the tongue so that the heat shield member is fixed in a heat exchangeable state. A structure for fixing such a cover is disclosed in Patent Document 2 instead of Patent Document 1.

  However, the ceramic heat shield requires a relatively large wall thickness in order to withstand the temperature of the hot gas generated in the stationary gas turbine permanently and reliably. When such a ceramic heat shield is used on both the tip and base platforms of the stator blades, this requires a relatively large turbine stator blade, correspondingly. Since a large space is required, the manufacturing cost increases.

  Patent Document 2 discloses the use of a shroud made of a superalloy. However, the cost of such a shroud is relatively high.

  In addition, as disclosed in US Pat. No. 6,047,089, a modular turbine blade with two sheet-like metal covers is transitioned to an associated platform half and blade blades that are curved with aerodynamic considerations. Covers the part. In this case, however, it is disadvantageous to seal the gap formed between the abutting platform halves of adjacent turbine blades by means of sealing elements inserted into the grooves. Although the type | mold which forms a flow path differs from this, it is disclosed by patent document 4. FIG. Patent Document 4 discloses that the platform half of the apparatus of Patent Document 3 can be omitted when one of the sheet-like metal covers is supported by adjacent turbine blades. For this reason, one platform half can be omitted. However, in the case of this development, the sheet-like metal cover is not always in close contact with the adjacent turbine blade.

European Patent No. 1219787 US Patent Application Publication No. 2007/0237630 EP 1557535 EP 1557534

  Accordingly, it is an object of the present invention to be relatively space-saving and to flow into the channel section with high reliability and safety, especially over a long period of time, without premature wear of the components forming the channel boundaries. An annular channel section for a turbomachine that guides hot gases.

  An object of the present invention is to provide an annular flow path for a turbomachine in which a shield element is arranged in a platform with a gap and a collision cooling hole is formed in the platform for collision cooling of the shield element Achieved by section.

  The present invention is based on the technical idea of protecting the platform half formed on the stator blade from the hot gas itself and the corrosion and heat effects of the hot gas even when the shield element is not made of ceramic. Yes. In this case, the shield element is appropriately cooled. In the present invention, the shield element is cooled by collision for the purpose of cooling. As a result of cooling the shield element, a thinner wall thickness can be achieved in the shield element compared to the prior art. By configuring the shield element walls to be relatively thin, space savings are achieved and cost effectiveness is enhanced. The blade blade of the corresponding stator blade can consequently be configured with a short span without reducing the channel cross-sectional area of the annular channel section in the present invention compared to the channel section based on the prior art. .

  Since the stator blade used in the flow path section in the present invention is usually manufactured by a molding process, most of the stator blade is integrally molded. Such stator blade platforms or platform halves conventionally not only withstand the pressure of hot gases, but also generate blade-fluid-induced forces-mechanical loads on the rear hook fixture It had a relatively solid wall, that is, a wall with a large wall thickness. For this reason, the cooling performance of the platform was poor, and the service life of the stator blades was previously limited by the platform. By utilizing the shield element of the present invention, the thermal load acting on the platform is reduced, thereby significantly improving the useful life of the stator blades.

  Furthermore, it occurs as a result of the corresponding curved portion, especially in the vicinity of the hollow fillet-like transition from the platform to the blade wing, especially in the case of flow passage sections that utilize stator blades without shield elements. The mass accumulation is only insufficiently cooled. Due to insufficient cooling performance of the transition part, fatigue phenomena such as cracks also occur in the transition part. Between the shield element and the blade blade wall or transition part, a cooling medium used to impingely cool the shield element, for example, cold air after the impingement cooling is completed, passes when it is discharged into the flow path. By using a shield element, the transition portion is better protected from direct contact and influence with hot gas flowing in the flow path. This reduces the thermal load at the transition from the platform to the blade blades, thus improving the useful life of the stator blades.

  In this case, each shield element extends over the entire gap, which is bounded by two directly adjacent stator blade platforms. Accordingly, even when the platforms adjacent to each other move due to thermal expansion, it is possible to reduce the loss that occurs when guiding the hot gas in the flow path.

  Further advantageous developments are described in the dependent claims.

  Preferably, the shield element has a metal base plate that forms the boundary of the flow path and is manufactured separately from the stator blades. The cooling performance of the shield element depends on the metal material. Furthermore, the entire shield element is manufactured separately from the stator blades. This means that if the wear phenomenon occurs on the shield element, only the shield element needs to be replaced, and it is necessary to replace it with a complete stator blade, as in the case of a stator blade platform without a shield element. It is advantageous in that there is no.

  The shield element is preferably made from a metallic material having good insulating properties.

  In a further advantageous development, the wall of the baseplate is thinner than the wall of the platform covered by the shield element. The thinner the shield element wall, the better the shield element is cooled by impact cooling. Further, by utilizing a relatively thin shield element, the flow section in the present invention requires less space compared to the prior art, so manufacturing costs and materials for such a flow path section. Cost is reduced.

  In a preferred development, a vertical wall section that can be connected to the side wall of the platform is provided at the edge of the base plate. Thereby, a shield element can be appropriately fixed to a stator blade.

  This is advantageous if the shield element has a protective coating, in particular a thermal barrier coating on the side of the flow path, in order to further improve the thermal resistance of the shield element to hot gases.

  The invention will be further described on the basis of exemplary embodiments represented in the drawings.

FIG. 4 is a cross-sectional view of two blade blades of the blade blade in the annular flow path section with the shield element disposed above the platform of the stator blade. FIG. 3 is a cross-sectional view of the stator blade platform and shield element in section II-II.

  FIG. 1 is a cross-sectional view of blade blades 14 of two stator blades 10 in an annular passage section 12 through which a hot gas flows in an axial direction of a turbomachine such as a gas turbine. The flow path section 12 basically includes a stator blade ring having a large number of stator blades 10 arranged continuously in the circumferential direction. FIG. 1 represents only two of the stator blades 10 among the stator blade rings known in many cases of the prior art. In this case, the stator blade 10 is fixed to the stator blade carrier by a conventional method. FIG. 1 is a cross-sectional view of the blade blade 14 and a plan view of the platform 16 of the stator blade 10. The shield element 22 is located between the blade blade wall 18 on the suction side of the stator blade 10 shown in the lower part of FIG. 1 and the blade blade wall 20 on the pressure side of the stator blade 10 shown in the upper part of FIG. It is arranged to adapt to the outer shape. The shield element 22 is basically formed in one piece, i.e. on the hot gas side, and has a half disposed below the platform 16 between the blade blades 14 of two directly adjacent stator blades 10. It is completely covered. For ease of understanding, only one shield element among the shield elements 22 arranged in the flow path section 12 is shown. In particular, the stator blade ring, in any case, has such a shield element 22 between each pair of blade blades 14 immediately adjacent. Further, adjacent shield elements 22 are adjacent to each other upstream of the leading edge 21 of the blade blade 14 and downstream of the trailing edge 23 of the blade blade 14 with a gap as small as possible.

  Furthermore, the collision cooling holes 24 are arranged in the platform 16 in a lattice shape, for example. FIG. 2 is a sectional view of the stator blade 10 and the shield element 22 in section II-II. The member names and reference numerals used in FIGS. 1 and 2 are the same. The shield element 22 is formed with a collision cooling hole 24 extending obliquely through the platform 16 in a state where a gap is formed between the shield element 22 and the platform 16 on the hot gas side, for example. Is placed on top. During operation of the turbomachine, the cooling medium K is sent to the rear gap 28 arranged on the opposite side of the flow path 26, and is thereby discharged from the rear gap 28 through the collision cooling hole 24, It flows as a jet jet into a gap formed between the platform 16 and the platform 16. Since the shield element 22 is cooled by the collision of the jet jet for collision cooling, the shield element can have an appropriate service life even though the high-temperature gas flows through the flow path 26.

  The shield element 22 represented as a cross-sectional view in FIG. 2 comprises a base plate 30 made of metal and extending in parallel to the flow path side surface of the platform. Wall sections 32 are provided at two edges of the base plate arranged opposite to each other, projecting at right angles to the base plate 30 at both edges and locking the corresponding side walls of the platform 16. Enclose to do. In this case, the wall of the base plate 30 is significantly thinner than the wall of the platform 16 in the vicinity of the collision cooling hole 24.

  In order to fix the shield element 22 to the stator blade 10 or the platform 16, the shield element 22 may be fastened by bolts, for example, as indicated by a dashed line. For example, other types of fixing methods may be used, such as tightening, in particular, the shield element 22 being fastened to the platform 16 in a fitted state. If desired, the shield element 22 may be provided with a thermal barrier coating on the surface of the shield element that is exposed to the hot gas to further increase the thermal resistance of the shield element.

  The cooling medium K flows into the gap formed between the shield element 22 and the surface of the platform, and after the impact cooling is performed, the shield element 22 and the blade blade wall 18 on the suction side or the blade blade wall on the pressure side. It flows out in the gap 36 (see FIG. 1) formed between the two.

  In this case, if the stator blade 10 utilized in the annular channel section 12 has a platform 16 extending at right angles to the blade blade 14 at both ends of the blade blade 14, FIG. And the shield element 22 disposed above the platform may serve as a rear end platform and a front end platform of the stator blade 10. Of course, the present invention may be used on only one of the two platforms of the stator blade 10.

  In summary, the present specification includes a stator blade ring having a large number of stator blades 10 arranged continuously in the circumferential direction. Annular passage section 12 for a turbomachine, with blade wings 14 projecting radially towards the, the boundary of the passage 26 being two directly adjacent on the platform side Formed by a shield element 22 disposed between the blade wings 14, and the shield element 22 forms a gap with the platform 16 to form a partially space-saving channel section 12. In the formed state, it is disposed above the platform 16, and a collision cooling hole 24 is disposed in the platform 16. Jo channel section 12 is disclosed.

DESCRIPTION OF SYMBOLS 10 Stator blade 12 Annular channel section 14 Blade blade 16 Platform 18 Blade blade wall on the pressure side 20 Blade blade wall on the pressure side 21 Leading edge 22 Shield element 23 Trailing edge 24 Collision cooling hole 26 Channel 28 Rear gap 30 Base plate 32 Wall section 36 Clearance K Cooling medium

Claims (5)

An annular flow passage section (12) for a turbomachine, a plurality of stator blades (10) arranged continuously in the circumferential direction, the blade root portion being provided for fixing, 2 Said stator blade (10) comprising at least one base platform (16) comprising two platform halves and a blade wing (14) projecting radially towards the interior of the flow path (26) In the flow path section (12) having
The boundary of the flow path (26) is formed by a shield element (22) on the platform side;
One of the shield elements (22) is disposed adjacent to the blade blade between two blade blades (14) that are directly adjacent to each other, and the stator that is directly adjacent Covering the gap bounded by the platform half of the blade (10);
The shield element (22) is disposed above the platform (16) in a state where a gap is formed between the shield element (22) and a collision cooling hole (24) is formed in the shield element (22). ) Is formed in the platform (16) in order to cool the collision. The shield element (22) has a base plate (30) made of a metallic material;
The flow path section (12) according to claim 1, wherein the base plate (30) forms a boundary of the flow path (26) and is manufactured separately from the stator blade (10). . The wall of the base plate (30) is thinner than the wall of the platform (16);
The flow path section (12) according to claim 2, wherein the platform (16) is covered by the shield element (22). A wall section (32) arranged at right angles to the base plate (30) is provided on the base plate (30);
4. Channel section according to claim 2 or 3, characterized in that the wall section (32) is connectable to a side wall of the platform (16).   The flow path section (12) according to any one of claims 1 to 4, characterized in that the shield element (22) has a protective coating on the side walls of the flow path.

Images