UA79816C2 - Recirculation appliance for turbo-compressors - Google Patents

Abstract

Disclosed is a recirculation structure for a turbocompressor, comprising an annular chamber which is arranged in the area of the free blade ends (25 to 28) of a blade ring and radially borders the main flow channel (29 to 32), and a plurality of guiding elements (37 to 40) which are disposed inside the annular chamber and are spread across the circumference thereof. Said annular chamber allows the flow to penetrate in the circumferential direction in the front and/or rear area. The guiding elements are connected in a fixed manner to at least one wall of the annular chamber but are detached everywhere else. The tips of the guiding elements, which face the annular chamber, run on and/or near the contour of the main flow channel while axially overlapping the free blade ends or axially bordering the area of the free blade ends.

Description

9. The recirculation device according to p. 8, which is characterized by details, primarily in the form of united segments of guide elements directed to the annular cavity, and removably fixed tops (41-44) of guide elements (37-40 ), in Lena in the ring chamber (29-32). in the case of their manufacture from light metal or synthetic 15. Recirculation device according to item 14, which cutting material, made with the possibility of encountering the fact that the guide elements (37-40) of expulsion with free ends (25-28 ) of blades made by forging or casting, or electrochemical allows the possibility of collision with them. processing and/or cutting processing. 10. The recirculation device according to any of items 1, 16. The recirculation device according to item 15, which is distinguished by 2, 4, 9, which is characterized by the fact that the annular chamber (29-32) is made to pass through flow in the circumferential direction of the ring by cutting and/or casting or forging. of the chamber is provided due to the presence of 17. The recirculation device according to any of clauses 1, holes (58, 59) in the front and/or rear parts 2, 4, 9, 13, 15, 16, which differs in that it in guide elements (37-40, 56). number of one or more pieces is located 11. The recirculation device according to any of item 1, stationary relative to the turbocompressor body, i.e. 2, 4, 9, which is characterized by the fact that the ring cam is made static, in the area of one or several ra (29-32, 53) and guide elements (37-40, 56) of the working wheels (20, 23, 24), and/or in quantity completed as one unit with the detail (5-7, 8 , 52), in which one or several pieces are located immovably, they are located. relative to the hub of the impeller of the turbocompressor 12. The recirculation device according to any of clauses 1, sora, i.e. made rotating, in the zone of one 2, 4, 9, which differs in that the annular cam- or several guide devices (15). ra (29-32, 53), together with the 18. Recirculation device according to any of item 1, straight elements (37-40, 56) located in it, the goal is fulfilled - 2, 4, 9, 13, 15, 16, which is distinguished by the fact that it is mono or in the form of at least two segments that are adjacent to each other in the circumferential direction, the annular chamber is provided by the presence of and is removably fixed on the part (5-7 , 8, 52), which carries notches (45-50). it is located 19. The recirculation device according to any of items 1, 13. The recirculation device according to item 12, which is distinguished from 2, 4, 9, 13, 15, 16, which differs in that it is made by casting, the continuity of flow in the circumferential direction, or by precision casting, cutting, or ring chamber (29-32, 53) is ensured by electrochemical processing. due to the presence of recesses (45-50) and/or holes (58, 2, 4, 9) in its front or front and 14. Recirculation device according to any of item 1, back parts (58, 2, 4, 9), which differs in that the electric guides 59), which are provided in the guide elements (37- ments (37-40) are made separately in the form of individual 40, 56). parts or combined into individual parts

The present invention relates to a recirculation As disturbances in the flow usually occur devices for turbocompressors, in particular, gas unevenly in the circumferential direction of the compressor stage of aircraft gas turbine engines and stationary, in addition to mainly axial recirculation gas turbines. lation from an aerodynamic point of view should be ensured

Recirculation devices for turbocompressors for compensation of such disturbances in the circumferential direction have been known for a long time and among specialists of the compressor stage. The main disadvantage of the well-known devices of the type "savzipd integrated in the body of recirculation devices, igeaitepi" (built into the body of recirculation - that is, devices of the type "sazipd igeaitepi", consists in us devices or anti-rupture devices). because they despite the provided by them

The main purpose of such devices is the possibility of increasing the surging threshold at the same time - expanding the area of aerodynamically stable operation, but at the same time reducing the efficiency. compressor. of the compressor due to the shift of the so-called border of the IU patent OE 3322295 SZ| the described axial surge to the side of higher pressure values, which the fan with built-in recirculation housing is created by the compressor, i.e. to the side by a higher device. Such a device has a ring of small compressor load values. Disturbance, ru (item 8) with memory elements fixed in it fixedly responsible for the occurrence of a local failure (item 93. On the back of the flow and in the final result for the occurrence of the flow in the area above the ends of the working blades of the compressor expansion , on the side of the body there is a zone open on the entire circumference, to which the ends of the blades of one impeller, respectively, the guide elements do not reach. Characteristic of several stages of the compressor, and on the side of the hub - a feature of a similar recirculator built into the body - on the radially inner ends of the blades of the working device is the presence of a closed wheel in it, because in these zones the aerodynamic ring (item 7), the contour of which lies approximately on the tension, reaches its maximum value. reduced energy and which separates the rear inlet part of the recirculation, which are located between the tops of the blades, and which of the lation device from and of the front output rotate with the frequency of their rotation, back into parts and forms a smooth continuous section by the main flow with an increase in their energy allows the upper. stabilize the flow again in the area of the ends of the blades.

In many respects, it is similar to the one described above, closing the guide elements in the circular recirculation device pressed into the body (known as direction. The free, radially inner edges are painted with OE 3539604 C1|, and in this case, in the direct elements (by 3. 21) have a chamfered in the front and rear parts of the ring chamber (item 7) straight from front to back, a shape that smoothly changes - there is an open area along its entire circumference. of the mentioned publication, the device also provides for the largest diameter of the annular chamber (item 16). not radially inner ring (item 6). Although in this case the guide elements on their

A more modern recirculation device built into the body of the section located closer to the output side and the lation device (known from patent O5 52827181. overlap in the axial direction with free

In the device described in this patent, its annular chamber is improved by aero-discs (item 14) of the blades on their located close to the entrance side of the site, but the presence of ve- (items 18, 28) and guide elements (item .24). However, the equal radial distance between the guide element - in this case, the input and output recirculation tams (pos. 21) and the ends (pos. 14) of the blades excludes flows separated from each other by a massive, smooth - the possibility of effective direction by the recirculator from the side of the blades closed ring The course of this flow in a certain direction. Another disadvantage of such rings in the case of touching the tops of this well-known device with them is that the blades must be equipped with a special coating on the opposite side of the blade-ring chamber (item 3z.16) of a large volume in the same area, nannies with the dimensions of the working blades . The device protects them from damage in the event of a collision with them. in turbocompressors.

Built-in recirculation device in the housing. Taking into account the characteristic known from the level of technology with a ring located in the area of the blades and having a solution to the shortcomings of the basis of this invention on its surface directed towards the blades, the task was set to develop a recirculating coating, A device for turbochargers is known from the application, which was approved by EP 0719907 A). In this application, such a ring would be able to significantly increase the surging threshold and due to what is considered as a pip agssaie tetreg ("the third of this is to significantly expand the area of stable operation of the arc-shaped element") (po. 3z.46), and the coating that the turbocompressor without appreciably reducing it contributes to running-in marked as "Iaueg oi k.k.d. abgadariye tagegia!" ("a layer of material that rubs off - This problem is solved with the help of retsirsya") (item 72). The guide elements marked in the circulator device for turbocompressors, indicated in the application as "mape waiY5" ("guides forward for gas turbines, which has a location") (item 64), are located radially outside the vane concentrically to the axis of the turbocompressor in the area of the ring (item 46) on its front and rear edges of the free ends of the blades of the vane ring crown (items 78 and 80). the chamber, the axial middle of which is located behind the

There are other devices built into the body by recirculating the flow in front of the axial middle of free circulation devices with grooves that run parallel to the ends of the blades and which in the radial direction are faceted to the axis, respectively at an angle to it, like this (described with a contour of the main flow channel, as, for example, in patent O5 5137419). However, the so-called ring space and the set of locations are not considered in this description, they are reflected inside the ring chamber and are distributed because of the presence of grooves in them that do not connect its circumference with guide elements, and at the same time, they are located between by themselves, do not allow the annular chamber in its front and/or rear parts to equalize the flow in the circumferential direction. the possibility of flow in it is provided

In patent 5 4511308) fans are described in a circumferential direction, and the guide elements are connected (blowers) with a recirculation built into their body, with at least one wall of an annular chamber, and lation devices of various designs. In most cases, they cantilever or freely protrude into it. in the simpler version, which is shown in Fig.b according to the invention, directed to the ring of the patent, the recirculation device of the cavity of the top of the guide elements is formed by only one ring chamber without on and/or near the line that limits the contour of the main guide elements in it. In other variants of the flow channel and in the axial direction shown in Fig. 1 and C of the specified patents, the guide elements overlap with the free ends of the blades or are fixed in this chamber, and in the axial direction border the zone, in to which the wall in front of them is arranged according to the course of the flow, the free ends of the blades are attached, while the relative (item 22) of the body is elongated in the form of a cylindrical, non-axial length of the ring chamber, which is measured according to the conical nozzle extending along the line, which limits the contour of the main proto-dialy inner edges of the guide elements of the internal channel to the axial length of the ends of the blades (pos. 3z.21), and therefore from the side directed towards the opposite side, the position is from 0.2 to 1.5. current, the front end of the annular chamber excludes the main feature of the proposed invention, the possibility of exiting the recirculation flow from it in the solution lies in the fact that the main flow is directed to the ring. In Fig. 5 of the specified patent, the top of the guiding elements of the index cavity are guided elements (item 21) that are attached to lie on, respectively, near the line that limits the front end wall of the annular chamber and to its contour of the main flow channel and in the axial bottom , and in the other cantilevered or freely projecting directions overlap with the free ends of the blade. In this case, the tubular part is not provided, or in the axial direction, it borders the zone, or the connecting ring element, corresponding to which the free ends of the blades are located. At the same time, there is no need to apply annular and strict requirements regarding their overall dimensions, elements equipped with coatings that protect the contour and other parameters, the size of the specified them from damage when they collide with the tops of the ratio should be chosen as minimal as possible, blades, and other elements . It follows from the above that is to perform an annular chamber of small radial- patent publications that in this region of depth. In the case of stationary turbocomputers, until now the main efforts for any springs, for the placement of which there are usually sufficient conditions, have been aimed at performing recirculation of a large space, the specified ratio of these devices from their directed to the main can be chosen closer to its upper limit . In the flow channel, i.e., to the so-called annular case of short in the axial direction of the annular space, the sides are smooth, those with chambers of the specified ratio should also be displaced by the minimum number of slits and are continuous in sections closer to its upper limit. these are of the maximum possible axial length with me- In the next best version, the front wall, which is the most rational from the point of view of aerodynamics, in the axial direction, and the rear wall in the axial direction and is associated only with minimal losses, the straight wall of the annular chamber is inclined, starting to lengthen the contour of the main flow channel . from their circular edges lying on the line that

In contrast to this, the proposed in the invention limits the contour of the main flow channel, the tension leads to the appearance of basically the same or different angle towards the flow (that is, the channel has slits, relief surfaces, etc. and is therefore tilted forward), which is from 30 to 60". At first glance, it seems unsuccessful and inappropriate. The guide elements are better to be performed in them. However, according to the results of the conducted experiments, it was established that the thickness proposed in the invention and with a certain cross-section profile . the recirculation device is superior to the known technical Guide elements, if you look at the axial solutions, both from the point of view of increasing the pump threshold in the direction, can be tilted under a certain mixture, and from the point of view of the efficiency of the turbocharger. - volume in the circumferential direction or curved in the circumferential view of the aerodynamics, a similar effect is possible in the direction, while the specified angle can be explained by the fact that the free, natural formation varies along the length of the belt elements and recirculation flow in an open annular hood is selected in such a way as to facilitate the measure with freely protruding guides from the aerodynamic point of view, i.e. to provide elements and flow connections in its vicinity - aerodynamically rational, the flow to the recirculation direction has much more important is the oscillating flow into the annular chamber. than the extension of the contour of the main flow- Directed to the annular cavity of the top of the channel with the minimum possible number of guide elements at least in the area of the slits. An additional advantage associated with the absence of recirculation vanes located radially opposite the free ends of the recirculation blades proposed in the invention, it is desirable to be radially distant from them on a solid ring device, consists in the absence of such a distance at which, during normal operation, there is no need to equip guide elements spe - the ends of the bocompressor are prevented from colliding with the blade coating, which protects them from damage to the guide elements. In this case, when the vanes collide with them, the possibility of damage to the tips of their working-in is taken into account, as well as in the reduction of the radial working vanes in the case of their contact with the sample dimensions of the turbocompressor and in the reduction of the number of solids that do not have the flexibility of the tops of its mass, which is connected with certain structural and guiding elements. Radial spacing ver- mechanical advantages. However, the direction of the reciprocations of the guide elements from the working tops of the lation flow to a certain, strictly specified side of the blades does not contradict the requirement, according to which the tops of the securing guide elements in the absence of ring elements should lie on the side only in the case when the free edges, directly near the line delimiting the main contour of many elements, are located relatively close to the flow channel, since the presence of a radial line to the edges of the blades and in the axial direction a gap of a small width between the vertices of the direction partially overlap with the edges of the vanes or their elements and the vertices of the working blades that at least border the zone in which it is located, which allows you to avoid their collision with each other, with the aerated edge of the blades. Only if this dynamic point of view is observed, there is practically no significant condition in the final result, it is possible to obtain a value, that is, it does not negatively affect the recircu- compact, suitable for its application in flow lation. turbocompressors have a reciprocating device built into their casing. The ratio of the axial length of the blade, such as steel or an alloy based on Mi or an annular chamber, to the axial length of the ends of the blade, made of a light metal such as AI or synthetic, should be between 0.2 and 1.5. In turbocom- material such as thermoplastic, reactive plastic springs with wide vanes with a large axial or elastomer. At the same time, directed to the annular length of their tops, this is the ratio of the cavity of the top of the guide elements, approaches 0.2, and in turbocompressors with narrow- if they are made of light metal or synthetic blades with a small axial length of their material, located so close to the peaks this ratio approaches 1.5. of the free ends of the blades, which is allowed

In the best version, the ratio of radial collisions with them. of the depth of the ring chamber to its axial length. The ability to pass the flow in the circular chamber should be from 0.1 to 1.0. During the development, the direction of the ring chamber is ensured by aviation engines, to which exclusively

due to the presence of holes in the front and/or rear, in comparison with the recirculation tines of the guide elements shown in Fig. 1. device

The ring chamber and guide elements can be made as one unit with the detail in Fig. 6 - a fragment of the one shown in the longitudinal view, in the section of the compressor in the area where they are located. built into its body recirculation

In one of the separate options, the annular camera device, modified in comparison with the recirculation elements shown in Fig. 1 and 5, is made in one piece or in the form of two segments that are adjacent to each other. to one in Fig. 7 - a fragment shown in the longitudinal, circumferential direction, and is removably fixed on a section of the compressor in the area where it is melted, in which it is located. built into its body recirculation

At the same time, the recirculation device can be a device, additionally modified in that it is made by casting, first of all, precisely compared to the ones shown in the previous drawings by casting, cutting, or electrochemical versions of its execution. processing The recirculation device 1 is shown in Fig. 1

In another separate variant of the implementation of the wine, the turbocompressor is built into the housing 5 and the guide elements of that stroke are made separately in the form of a device of the type "savipd of individual parts or united in an individual-igeaitepe" (English "savipd" - body). The flow direction of the group of parts, primarily in the form of a unified main flow channel 9, in which the guide elements are melted into segments, and a removable system of vanes, marked as shown on fixed in the annular chamber. In this case, drawing to the left with an arrow, that is, the flow moves straight elements can be made through this channel from left to right. In the area shown in the drawing by casting or electrochemical processing, the flow first encounters the direct and/or cutting processing, and the annular chamber is the output device 13 (input), then the working wheel is processed by cutting and/or casting or forging 20 and then on one more guide device 14 (output). The radially outer contour of the main 11

In one of the options for using the recirculation flow channel 9 corresponds to the internal con- the device can be in the amount of one or a tour of the housing 5 and for clarity conventionally marked several pieces are located motionless relative to the drawing with dash-dotted lines that pro- the turbocharger housing, i.e. made statically extend it to the left and right of the main image, in the area of one or more working wheels of the image. The static recirculation device and/or in the amount of one or more pieces is located 1 interacts with the impeller 20 and in the axial direction fixed relative to the hub is mostly located in front of it, the wheel of the turbocharger, i.e. performed in front of the flow. With a radial return, in the zone of one or more guides on the opposite side to the main flow channel 9 ratas. an annular chamber 29, open from its side, adjoins,

The ability to pass the flow in the circular, which together with the guide elements 37 and forms the direction of the ring chamber, is ensured by the recirculation device 1. The tops 41 of the guides of the presence of notches, in particular due to the existing elements 37, lie on the same line as those in its front or front and rear parts limit the contour 11 of the main flow channel 9, recesses and/or holes provided in the guides or near it, that is, at least approximately elements. lie on the line that limits the inner contour

Below, the invention is considered in more detail from the case. These guide elements 37 can be a reference to the attached simplified and made made of metal, for example nickel alloy, without observing the scale of the drawing, on which light metal, for example aluminum, or of synthetic material, such as thermoplastics, reactive - in Fig. 1 - a fragment shown longitudinally - layers or elastomers. The front 33 and the rear 34 are sections of the axial-type compressor in the section, the walls of the annular chamber 29 to reduce their ae- on which the recirculation device built into its body is located, marked with a small recirculation device, an arrow, the recirculation flow is inclined - Fig. 2 - similar to the fragment shown in the radially inward drawing shown in the previous drawing in the longitudinal edges 35, 36. of the compressor in the area where the angle of inclination of the front wall is indicated by the tash built into the hub and can be equal to angle of inclination of the back wall 34 recirculation device, or differ from it. Between the front wall in Fig. 3 - a fragment of the cross-section shown in 33, guide elements 37 and the back wall of the recirculation device, which is shown in 34, recesses 45, 46 are provided, which, in addition to those in Fig. 1, recirculate flows, which takes place mainly in Fig. A - a fragment of Fig. 1 and C in the axial direction, allow their movement in the annular recirculation device in the form of a radially c- chamber in its circumferential direction. The position 25 of the middle, the free ends of the blades of the impeller 20, in the zone in Fig. 5 - a fragment of the shown along which the most probable occurrence of disturbances in the cross section of the compressor in the section on which outlet. The area of mutual axial overlapping is marked with a marking device built into its body of the recirculating guide elements 37 and the ends of the blades 25, modified to some degree in Fig. 1 as ОЕ1.

In contrast to the variant shown in Fig. 1, this flow in this case must be twisted

Fig. 2 shows a recirculation device 2 integrated into the rotating hub against the rotation of the impeller 20. Position-8 recirculation device 2. In the shown on it 36, the rear edge of the flow is marked in this drawing version in the main flow ring chamber. channels 10 are located, if you look from the left to the recirculation device shown in Fig. 5 From the right, the impeller 21, which directs the device 15, is built into the recirculation body, the free ends 26 of the blades of which are directed radially device with a turbocomp integrated into the body 6 - inside, and the impeller 22. According to the spring, the annular chamber 31. In this case, a similar recirculation device with such guide elements 39 reach the front wall, its new location should be marked with the annular chamber 31, in the rear part which can be read as a device of the "pyr igeaitepi" type (a device located directly near the ends of the 27 blades of the working English "pyr" - a hub), i.e. as built into the wheels 23 there are notches 49. Through the SHEZ in the drawing, the hub is a recirculation device. This recirculation is a marked section of the axial mutual overlap device 2, which consists of a ring of guide elements 39 with the ends 27 of the blade chamber 30 and guide elements 38 with front currents. Through IR, the drawing shows the axial longitudinal and rear recesses 47, 48, which are present between the front wall of the annular chamber 31, and through NE, it is marked by its front and rear walls of the annular chamber 30 and the radial depth. The axial length of the ends of the blades 27 is measured through I 5 on the drawing, marked by guide elements 38 that are distant from them. The relationship interacts with the guiding apparatus 15, that the thickening of the value of IR to the value of Г5 should be what is located downstream of the flow behind it. Oski - from 0.2 to 1.5, and the ratio of the value of NE to large in this case is from 0.1 to 1.0. In the considered version, the circulation device rotates, and the guide guide elements 39 to avoid their collision with the apparatus 15 remains stationary, the frequency of the rotating ends of the blades 27 are made slightly shortened and the melting of the rotor fully corresponds to the relative frequency radially outward with stepped tops 43, rotation. According to its principle of operation, the recirculation device built into the radial hub does not differ from the recirculation device built into the body during their rotation. Positions 16 and 17 indicate the pulsation device. Recirculation devices, guiding devices. of both types, i.e. built into the body and insert- Shown in Fig.b6 recirculation device 4 ny into the hub recirculation devices, can with the ring chamber 32 and guide elements also be used together in the same 40 is also a recirculation device, turbocompressor, in including in several of its built-in body 7 turbochargers and which stages. In the case under consideration, it radially interacts with the impeller 24. In contrast to the inner contour 12 of the main flow channel of the variant shown in Fig. 5, the guide elements 40 correspond to the outer contour of the hub 8. In this case, the sections reach the back wall of the mutual ring the axial overlap of the guides of the bow chamber 32. The recesses 50 formed by the ra- elements 38 with the ends 26 of the guide vanes of the guide elements 40 from the spacer 15 are marked on this drawing through the front wall of the ring chamber 32,

THIS2. In the places of the transition to the walls of the ring chamber, in the considered variant, the front guide elements 38 are located to increase their strength. In this version, the tops 44 of the guide rods are made in their base in such a way that the expanding elements 40 overlap with the zone in which the radius is, that is, with the halyards. the ends of 28 blades are cut.

Figure 3 shows in more detail in section the recirculation device shown in Figure 7, a fragment of the structure shown in Figure 1. Direction 51 differs from the options considered above in that the elements 37 are inclined at such an angle B to its execution that in the front and rear parts of the radius, at which the ends of the blades 25 of the working elbows of the guide elements 56 are provided entirely with 20, which rotates ( in the one indicated by the arrow, the holes 58, 59 are closed along their perimeter, which direct the recirculation without significant losses - provide the possibility of movement of flows in the annular flow into the annular chamber 29. When the chamber 53 is in its circumferential direction. Thus, the curvature of the guide elements, the angle of their inclination, in this version, there are jumpers 60, 61, which can decrease in the radial direction from the middle, increase the strength of the guide elements 56, and outwards to zero value. but connecting them to the front and back walls 54,

In principle, there is a possibility of a strictly radial 55 annular chamber 53, which is made in the housing 52 of the location of the guide elements, that is, from the turbocharger. In another option, instead of one angle of their slope B, which is equal to 0", however, such a hole 58, respectively 59, it is possible to provide an arrangement that is less expedient from the point of view of aerodynamics - the notch described above, formed due to the effective resistance created by them installation of guide elements with a deviation from the

A more visual representation of the aerodynamics of one wall of the annular chamber 53. Obviously, the profile and curvature of the guide elements 37, so that in the guide elements it is possible to obtain the projection shown in Fig. 4, where only one hole 58 can be provided, - the appendix to Fig. 3 shows the profile of the blades, respectively 59 in their front or rear part. what wheels 20 along with the direction of its rotation In all versions of recirculation (marked by an arrow). For a specialist, it is obvious that the tops 41-44 and 57 of the guide elements are located at the exit from the annular chamber 29 in the area of its ends 37-40 and 56, provided they are made from the soft front edge 35 of the recirculating metal or synthetic material

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Ministry of Education and Science of Ukraine

State Department of Intellectual Property, str. Urytskogo, 45, Kyiv, MSP, 03680, Ukraine

SE "Ukrainian Institute of Industrial Property", str. Glazunova, 1, Kyiv - 42, 01601