JPS58500489A - floating inflation control ring - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] floating expansion control ring Technical field TECHNICAL FIELD This invention relates generally to turbine engines and more particularly to gasifier turbines of gas turbine engines. Concerning an expansion control ring that is mounted around the bottle.

In order to operate a gas turbine engine effectively, the turbine blades and the surrounding engine are Relatively tight tolerances must be maintained between them. This is the end of the turbine blade and To minimize power loss due to expanding gas passing between the surrounding shrouds is necessary. In a turbine engine, the expansion of the turbine impeller relative to the engine is by design. This is a problem that must be addressed during and in some cases during engine operation. Main departure Although the specification specifically deals with gas turbine surrounds, it is equally applicable to steam turbine surrounds. Ru.

As mentioned above, the efficiency of a gas turbine engine is determined by the efficiency of the gas flow through the gasifier turbine. tightness]. The hot gas flows through the turbine impeller and extends into the turbine. There is considerable expansion of the turbine voice wheel when it hits the blades. Turbine impeller and circumference Several measures are taken to maintain tightness between the surrounding turbine shroud structures. can be taken. First, the expansion ratio of the turbine shroud structure is It is appropriate to attempt to ensure that the tension ratio is essentially the same as or slightly greater than It is. To achieve this, the turbine shroud structure is It is necessary to design it to expand equally through the boundaries. The structure of this type is 1 "Target" granted to Karl w, xarsten8en on February 17, 981. U.S. Patent 4,251.185 for ``Inflation Control Ring for Bin Shroud Assembly'' is taught.

The structure disclosed in the above-mentioned patent allows expansion of the shroud P assembly concentric with the engine axis. However, it may cause temporary eccentricity of the turbine impeller during engine acceleration or deceleration. turbine blades and shroud to compensate for transient mismatches in the expansion of the turbine impeller. does not preclude the need for some kind of additional gap in between. Therefore, in the above-mentioned patent, Peelable shroud structures are also utilized. Such a shroud structure is similar to that of a turbine blade. Allows contact of various turbine blades with the shroud structure without undue damage to the roots. vinegar. In particular, the abradable portion of the shroud structure is made softer than the turbine blades. Therefore, the shroud structure wears out during such contact.

In other applications, the tips of the turbine blades are subject to wear. It is designed to. These types of turbine blades are connected to the turbine shroud. It is commonly referred to as a "squeal tip", which derives from the fact that it produces a "squeal" when touched.

The only drawback of "squeal tip" blades is that the cooling passages typically found in gasifier turbine blades This is because they are easily blocked by abrasion at the tip of the turbine. The cooling passage is turbid. If the turbine blades become blocked in the turbine blades, the turbine blades will overheat and then fail.

Both the abradable shroud type structure and the "squeal tip" type structure allow the turbine blades to The gap between the car and the shroud structure is either the shroud structure or the turbine tip. contact between the turbine impeller and shroud structure sufficient to cause metal abrasion at Perpetually increased each time. Not only is there a permanent increase in the gap, but there is also abrasion. The particles may damage the power turbine downstream of the gasifier turbine. Ru.

The above illustrates the limitations of known prior art. Therefore, an alternative to the prior art It is clear that it is advantageous to provide.

Disclosure of invention In one aspect of the invention, this includes a pair of manifold rings and a manifold ring. a floating expansion in the turbine shroud assembly having a spacer ring disposed between the This is achieved by providing a tension control ring. Furthermore, multiple spacer rings cutouts are defined on its inner periphery, each cutout having a depth D and a width WY-Nj. .

The expansion control ring has a plurality of ledges extending outwardly from its outer periphery, each having a The ledge has a width less than the width of the ledge or cutout.

In previous Daca turbine shroud assemblies, the turbine blade and shroud structure abradable shroud segments or on turbine blades to overcome contact between It is necessary to include either an abradable tip.

The present invention makes the shroud structure eccentric to the engine axis via a floating expansion control ring. to maintain concentricity with the turbine impeller.

The above and other aspects will be apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings. It will become clear. However, the drawings are not intended as a limitation of the invention. It should be clearly understood that this is not intended for illustration purposes only.

Brief description of the drawing FIG. 1 is a portion of a turbine shroud assembly forming an embodiment of the present invention.

FIG. 2 depicts associated mounting elements which together with the turbine blade form an aspect of the invention. FIG. 2 is a cross-sectional view of a turbine shroud assembly.

FIG. 6 shows an expansion control ring forming an embodiment of the present invention and associated shutters of the prior art. Figure 3 is a series of schematic diagrams of loud structures;

Referring to FIG. 1, a portion of a turbine shrouge assembly 100 is illustrated.

A turbine shroud assembly, such as shroud assembly 10 shown in FIG. A plurality of vanes 12 are then impinged by the flow of hot gas, as indicated by G. A turbine impeller 11 extending outwardly (schematically shown in Figures 4A-1dE) For use in gas turbine engines, % It can be applied to

As shown in FIG. 1, the shroud assembly 10 has three main parts: a spacer; ring 14, a pair of manifold rings 28 and 30, and an expansion control ring 20. Become. The spacer ring 14 is the outermost part and has a plurality of notches 16 therein. each formed on the outwardly extending webs 32 of the expansion control ring 20. The corresponding projection 18 is received.

The expansion control ring 20 has a plurality of shroud segments 22'Y disposed thereon. Njru. The shroud segment 22 and expansion control 20 are secured to the surrounding engine. A floating interface is provided between spacer ring 14 and rotating turbine blades 120.

Referring now to FIG. 2, the expansion control ring 20 and associated shroud segments It can be seen how the bolt 22 is floatingly attached to the engine casing 24.

The spacer ring 14 has a plurality of holes 27 through which corresponding bolts 27 can pass. is forming. Manifold IJ 7g 28 on each side of spacer ring 14 and 30, respectively. The purpose of these manifold rings is as described in U.S. Patent No. 4.2. It is more clearly described in No. 5 Ll No. 85. These rings or shrouds In addition to providing 3D support, it also helps direct cooling air to the shroud assembly. Let's just say that.

As can be seen in FIG. 2, bolts 27 are attached to manifold rings 28 and 30 and through the engine casing 24 and is thus attached to it. .

The spacer ring 14 is slightly thicker than the thickness T2 of the web 32 of the expansion control ring 20. It has a large dimension T1. With this large thickness, manifold rings 28 and 30 and spacing movement of the expansion control ring 20 relative to the thermal ring 14.

Next, referring to FIG. 6, an enlarged view of the expansion control ring 20 is shown in the spacer ring. 14. The expansion control ring 20 has an outer circumference 3 having a radius R1. 4, the spacer ring 14 has an inner periphery with a radius R2. Radius R2 It is clear that R is larger than the radius R by a predetermined amount. Similarly, in Figure 6 Each ledge 18 has a width W1'&1N, while each notch 16 has a width W1'&1N. It can be seen that it has W2. Furthermore, the depth of each notch is equal to the predetermined measurement. while the height of each bulge is equal to H.

Therefore, the relationship between each notch and each ledge is It can be defined as. Ru.

This gap relationship is the gap that controls the radial movement of the expansion control ring (W2 pull < Wl). ’ occurs.

The parts assembled as described above provide an expansion control link in a gas turbine engine. The rod 20 may move eccentrically as described in the next paragraph.

Referring now to FIG. 4A, the expansion control ring is schematically illustrated as a circle at 20. , -10,000 spacer rings are also schematically illustrated as circles at 14. related tar A schematic turbine impeller 11 with bin blades 12 is shown in a rest position in FIG. 4A. has been done. Abrasion as described in U.S. Pat. No. 4,251,185, cited above. Prior art devices with shroud segments that can If there is no concentricity between the turbine shroud 20' and the turbine impeller 11', then For example, take the shape shown in Figure 4B. In particular, in FIG. 4B, the turbine impeller 11 ' moves downward and the associated turbine blade 12' contacts the expansion control ring 20'. It can be understood that Due to the abradable construction, the expansion control ring then As shown in Figure C, it loses its circular shape.

The state in which the blades and turbine impeller have lost their circular shape is shown in Figure 4C. The increased gap between the two causes a loss in efficiency of the turbine engine. In Figures 4A-4E It is understood that the illustrations have been exaggerated to better clarify the problem.

If it is a "squeal tip" type vane as described in detail in this invention, the result is a 4D The length is reduced around the entire root wheel by referring to the diagram. When this happens, the effect The loss in rate is much greater than in the embodiment shown in Figure 4C. In Figure 4D The "squeal tip" blade 1γ is worn out, and the blade IZ' and expansion control ring 2σ' The gap between them is increased concentrically. Of course, spacer ring 14'' and turbo The impeller 11'' remains unaffected.

The invention is schematically illustrated in FIG. 4E, where the turbine impeller 11 is The housing is eccentric with respect to the housing as indicated by the housing ring 14. Tar As a result of the eccentricity of the bottle impeller 11, as best shown in FIG. Initial contact occurs between the shroud segments 220 and 200, and expansion control ring 20 from its concentric position to an eccentric position with respect to the engine axis 40. Despite the resulting movement, the concentricity of the turbine impeller 11 is maintained.

As the turbine impeller returns to concentric relationship with the turbine axis 40, the expansion control link The gear 20 may move or float relative to the turbine impeller. For this reason, the ledge 18 The notch 20 is formed when the turbine impeller 11 is operated eccentrically with respect to the engine axis 40. The expansion control ring 200 also maintains overall concentricity with the turbine impeller 11. I will provide a.

1 and 6, the expansion control ring 20 moves radially. It is understood that the rotation can be performed in the axial direction by a degree of 1. . At the same time, sufficient clearance exists between the expansion control ring 20 and the spacer ring 14 for expansion. Changes in ratio can occur without significant damage to internal parts of the engine. Projection 18 and notch The gap between the sides of the notch 16 is smaller than the gap between the notch 16 and the end of the ledge 18. Therefore, it is appropriate to control the radial movement of the expansion ring by means of side clearances. Ru. Also, the fit should be tight enough to prevent movement between the two parts. Make sure that the gap between the tension and the sides of the notch is not made so large that there is excessive movement. It is important to understand.

The above-described invention is based on a "squeal tip" or an abradable shoe as described in detail in the present invention. It is particularly advantageous in overcoming the need to use either loudspeakers. In the past, Strippable shrouds are susceptible to oxidation or corrosion due to high gas temperatures and After a short period of time it is undergoing erosion due to high gas velocity. In this way, the fourth In addition to the possibility of permanent eccentricity as shown in Figure C, the turbine impeller and expansion The actual clearance between control rings 200 increases due to this erosion and corrosion problem. "Sound" If "tips" are used for all the blades of the turbine impeller, as shown in Figure 4D. As such, there is a permanent increased gap between the shroud structure and all vanes. Furthermore , when there is a cooling passage provided in the turbine blade 12, the circumference of the end of the "squeal tip" The abrasion of the blades blocks the airflow through the turbine blades 2 and has a detrimental effect on the cooling of the engine itself. Two.

Although the present invention has been described in terms of preferred embodiments, it is possible to use other elements thereof without departing from the scope of the invention. It will be appreciated by those skilled in the art that various changes may be made to the same and equivalents may be substituted. be understood by those who In addition, many modifications may be made to accommodate special conditions and materials of the present invention. It may be done to adopt the doctrine without departing from its scope. Therefore, the present invention discloses Without being limited to the specific embodiments described, the invention falls within the intended scope of the claims. It is intended to include all aspects.

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Claims (1)

[Claims] 1. A pair f) Manifold *Jl 7ri c211.30) a spacer ring (14) disposed between the rings (28, 30); Multiple outward extending ledges (18) 'f! floating expansion control ring (20) , said spacer ring (14) has a corresponding compound for receiving said ledge (18). defining several cutouts (16), said cutouts (16) forming said spacer; each of the notches (16) being formed on the inner periphery of the ring (14); has a width greater than the width of the corresponding ledge (18) of the expansion control ring (20); and A turbine system consisting of shouldering a depth greater than the height of the corresponding ledge (18). enclosure assembly. 2. The spacer ring (14) has an inner diameter R2Y and the expansion control ring (20) It has an outer diameter R1, and each of the protrusions (18) extends outward beyond a radius RIY equal to H. extending a long distance, each of said ledges (18) having a width Wl, each cut The notches (16) have a depth D and a width W2Y, and each notch (16) and each The relationship between the projecting points (18) is The turbine shroud assembly of claim 1 defined as: 3, a pair of manifold rings (28, 30), the manifold rings (28, 3); 0) has a spacer ring (14)'Y disposed between the spacer ring (14)'Y; 4) is defined by a plurality of notches (16)' on its inner periphery, and the inner periphery has a radius R. 2Y, and each notch (16) has a depth D and a width w2y, - a floating expansion control ring (20), said floating expansion control ring; the ring (20) has an outer periphery with a radius R1, and R1 is smaller than R2; An expansion control ring (20) has a plurality of outwardly extending ledges (1) at the outer periphery. 8)' & each of said ledges (18) has a width Wl and a height H'a' [If W is smaller than W2 and H is smaller than or equal to D, good. 4. The relationship between each notch (16) and each tension (18) is Claims Defined as Improvements. 5. Defining an axis...Using, which is rotatably installed in the housing in the axial direction. a turbine impeller attached thereto, and around said axis and around said turbine impeller; a shroud assembly concentrically attached to the In a turbine engine including a control ring, the turbine impeller is relative to the engine axis. moves eccentrically and keeps the expansion control ring generally concentric with the turbine impeller. An improvement consisting of means for causing