Rotor blade assembly comprising a ring-shaped or disc-shaped blade carrier and a radially inner reinforcement structure

Abstract

A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.

Claims

1. A rotor blade assembly group for an engine, comprising: a ring-shaped or disc-shaped blade carrier including a plurality of rotor blades that are provided along a first circle line about a central axis of the rotor blade assembly group, the blade carrier including a carrier section that extends radially inwards in a direction toward the central axis with respect to the plurality of rotor blades, the carrier section comprising a connection area positioned at a radially innermost portion of the carrier section farthest from the plurality of rotor blades, at least one stiffening ring fixedly attached at the connection area of the carrier section, the at least one stiffening ring being arranged at a first or a second face side of the blade carrier, and the connection area of the carrier section including a profile that includes at least one axial projection, with the profile having a T-shaped, I-shaped, or fir tree shaped cross-section, the at least one stiffening ring engaging around the profile in a form-fit manner, such that the at least one axial projection is received at least partially between a radially outer section and a radially inner section of the at least one stiffening ring, wherein the blade carrier includes a passage hole that extends axially with respect to the central axis and that is radially delimited by a radially innermost edge of the carrier section, and a portion of the radially inner section of the at least one stiffening ring axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section, wherein the at least one stiffening ring is separate from a connection component that connects the blade carrier to at least one other adjacent blade carrier.

2. The rotor blade assembly group according to claim 1, wherein: the at least one stiffening ring includes a first stiffening ring and a second stiffening ring, the first stiffening ring and the second stiffening ring fixedly attached at the connection area of the carrier section, the first stiffening ring is arranged at the first face side of the blade carrier and the second stiffening ring is arranged at the second face side of the blade carrier, such that the second face side is facing away from the first face side, and the first and second stiffening rings are connected to the connection area of the carrier section and in addition are connected to each other.

3. The rotor blade assembly group according to claim 2, further comprising a fastener connecting the first and second stiffening rings to each other.

4. The rotor blade assembly group according to claim 3, wherein a section of the fastener axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section.

5. The rotor blade assembly group according to claim 3, wherein the fastener at least partially encloses the first and second stiffening rings, such that at least parts of both the first and second stiffening rings are received between two respective sections of the fastener in a cross-section along the central axis.

6. The rotor blade assembly group according to claim 3, wherein the fastener is formed as a spring tensioner supported at both the first and second stiffening rings in a form-fit matter or a force-fit matter, and such that the spring tensioner exerts a force on at least one of the first and second stiffening rings, the force acting in a direction toward the other of the first and second stiffening rings.

7. The rotor blade assembly group according to claim 2, wherein at least one of the first stiffening ring and the second stiffening ring is made of a metal matrix composite.

8. The rotor blade assembly group according to claim 2, wherein at least one of the first stiffening ring and the second stiffening ring includes an internal core made of a metal matrix composite.

9. The rotor blade assembly group according to claim 8, wherein the at least one stiffening ring that includes the internal core made of the metal matrix composite is configured such that the internal core made of the metal matrix composite axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section.

10. The rotor blade assembly group according to claim 1, wherein the profile of the connection area of the carrier section that has the T-shaped, I-shaped, or fir tree shaped cross-section extends along a second circle line about the central axis of the rotor blade assembly group at least in certain sections.

11. A gas turbine engine with at least one rotor blade assembly group according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The accompanying Figures illustrate possible embodiment variants of the invention by way of example.

(2) FIG. 1 shows, by sections and in a sectional rendering, a part of a turbine of a gas turbine engine with two embodiment variants of a rotor blade assembly group according to the invention.

(3) FIGS. 2A-2C shows, in enlarged rendering and by sections, a connection area of a blade carrier with different variants of a stiffening structure with MMC stiffening rings arranged thereat.

(4) FIGS. 3A-3B shows, by sections and in sectioned perspective view, embodiment variants of a blade carrier of a rotor blade assembly group according to the invention with a firtree-shaped profile of the connection area, wherein, on the one hand, the blade carrier has rotor blades (FIG. 3A) that are formed integrally therewith and, on the other hand, is provided for separately manufactured rotor blades which are to be fixated thereat (FIG. 3B).

(5) FIG. 4 shows, in sectioned and enlarged view, a variant of a connection area of the blade carrier with a firtree-shaped profile.

(6) FIG. 5 shows, by sections and in a sectioned rendering, a design of rotor blade rows of a turbine of the gas turbine engine as it is known from the state of the art.

(7) FIG. 6 shows a cross sectional view of a turbine engine in which one embodiment variant of a rotor blade assembly group according to the invention is used in the area of a compressor and/or in the area of a turbine.

DETAILED DESCRIPTION

(8) FIG. 6 schematically illustrates, in a sectional rendering, a gas turbine engine T in which the individual engine components are arranged in succession along a rotational axis or central axis M. By means of a fan F, air is suctioned in along an entry direction E at an inlet or an intake E of the engine T. This fan F, which is arranged inside a fan housing, is driven via a rotor shaft S that is set into rotation by a turbine TT of the engine. Here, the turbine TT connects to a compressor V, which for example has a low-pressure compressor 11 and a high-pressure compressor 12, and where necessary also a medium-pressure compressor. The fan F supplies air to the compressor V, on the one hand, and, on the other hand, to a secondary flow channel or bypass channel B for generating a thrust. Here, the bypass channel B extends about a core engine that comprises the compressor V and the turbine TT, and also comprises a primary flow channel for the air that is supplied to the core engine by the fan F.

(9) The air that is conveyed via the compressor V into the primary flow channel is transported into the combustion chamber section BK of the core engine where the driving power for driving the turbine TT is generated. For this purpose, the turbine TT has a high-pressure turbine 13, a medium-pressure turbine 14, and a low-pressure turbine 15. The turbine TT drives the rotor shaft S and thus the fan F by means of the energy that is released during combustion in order to generate the necessary thrust by means of the air that is conveyed into the bypass channel B. The air from the bypass channel B as well as the exhaust gases from the primary flow channel of the core engine are discharged via an outlet A at the end of the engine T. Here, the outlet A usually has a thrust nozzle with a centrally arranged outlet cone C.

(10) As is known, rotor blade assembly groups which rotate about the central axis M and respectively have one rotor blade row and in which the rotor blades are provided at a ring-shaped or disc-shaped blade carrier, are used in the area of the (axial) compressor with its low-pressure compressor 11 and its high-pressure compressor 12 as well as in the area of the turbine TT. In principle, the ring-shaped or disc-shaped blade carrier can be integrally bladed, and can thus be manufactured in Bling or Blisk design. Alternatively, it is possible to fixate individual rotor blades at a ring-shaped or disc-shaped blade carrier via their respective blade roots. For this purpose, a blade root may for example be axially inserted into a fastening groove of the blade carrier and axially secured at the respective blade carrier.

(11) By way of example, FIG. 5 illustrates multiple rotor blade assembly groups 2a, 2b and 2c of the turbine TT arranged behind each other along the central axis M. Here, the section that is shown in FIG. 5 depicts only a part above the central axis M in the area of the medium-pressure turbine 14 or the low-pressure turbine 15. The individual rotor blade assembly groups 2a, 2b and 2c are connected to each other in a torque-proof manner via flange connections 4.1 and 4.2. Further, each rotor blade assembly group 2a, 2b and 2c has respectively one ring-shaped or disc-shaped blade carrier 23, 24 or 25, at which individual rotor blades 20, 21 or 22 of a blade row are arranged behind each other along a circle line about the central axis M, and at which respectively blade carriers 23, 24 or 25 are fixated via a blade root 200, 210 or 220 of a rotor blade 20, 21 or 22. In the axial direction along the central axis M, rotor blade rows of the rotor blade assembly groups 2a, 2b and 2c alternate with stationary guide vane rows. The guide vane rows respectively have guide vanes 30 or 31 that are also arranged along the entire circumference on a circle line about the central axis M.

(12) Due to the rotational speeds and the resulting loads, each blade carrier 23, 24 or 25 of a rotor blade assembly group 2a, 2b or 2c of the state of the art has a radially inwardly extending carrier section 230, 240 or 250. A disc-shaped carrier section 250 of the rear rotor blade assembly group 2c for example serves for the rotatable mounting of the rotor blade assembly groups 2a, 2b and 2c that are connected to one another in a torque-proof manner. In the carrier section 230, 240 of two (with respect to the flow direction through the engine T) frontal rotor blade assembly groups 2a and 2b, a central passage hole O1 or O2 is provided mainly for the purpose of weight reduction, for example in the form of a bore. With view to the necessary installation space of the rotor blade assembly groups 2a and 2b as well as their weight, it is most important which radial extension the blade carriers 23 and 24 have in order to be able to withstand the loads that occur during operation.

(13) In the different variants of a solution according to the invention, which are for example illustrated in FIG. 1 by way of example based on two rotor blade assembly groups 2a and 2b of the turbine TT, a considerable size reduction of the radially extending carrier sections 230 or 240 is achieved by providing a stiffening structure 5a or 5b. Here, both different variants are illustrated together in FIG. 1. However, it is not obligatory that different stiffening structures 5a and 5b are provided at a rotor blade assembly group 2a and another rotor blade assembly group 2b. In practice, it will be advantageous to use identically embodied stiffening structures 5a or 5b at different rotor blade assembly groups 2a and 2b to render the mounting easier and to be able to use as many identical parts as possible.

(14) However, what different variants of stiffening structures 5a and 5b respectively have in common is that two ring-shaped stiffening elements, which are positioned opposite each other, are arranged in the form of (MMC) stiffening rings 50 and 51 at the face sides of the respective blade carriers 23 or 24. On the one hand, the stiffening rings 50 and 51 are directly connected to each other, preferably via at least one additional connection element. On the other hand, both stiffening rings 50, 51 respectively enclose one connection area 231 or 241 of the respective carrier section 230 or 240 in a form-fit manner at least in certain sections, with the carrier section 230 or 240 having a continuous profile in the circumferential direction that comprises at least two projections axially extending in opposite directions. Here, in the one variant of the rotor blade assembly group 2a, the connection area 231 is provided with a firtree-shaped (cross sectional) profile, while in the other rotor blade assembly group 2b of FIG. 1 a T-shaped cross sectional profile is provided.

(15) As is illustrated based on FIGS. 2A, 2B and 2C for different variants of the stiffening structures 5a, 5b, each stiffening ring 50, 51 of the respective stiffening structure 5a or 5b has a coated MMC core 500, for example a TiMMC core. By manufacturing the stiffening rings 50 and 51 in MMC design, a considerably increased stiffness of the blade carrier 23 or 24 is achieved, while at the same time it has a comparatively low weight. In each of the variants of the FIGS. 2A, 2B and 2C, a stiffening ring 50 or 51 axially extends with a enclosing section 50.1 or 51.2 below an edge of the connection area 231 or 241 that is facing towards the respective passage hole O1 or O2 in the direction of the other face side. Thus, each stiffening ring 50 or 51 at least partially encloses a radially internal edge of the respective blade carrier 23 or 24 in an L-shaped manner. In this manner, in particular the radial securing of the respective stiffening ring 50, 51 at the carrier section 230 or 240 is facilitated, and a support of the blade carrier 23, 24 below of the connection area 231, 241 is also achieved.

(16) In the present case, both stiffening rings 50 and 51 extend so far axially below the inner edge of the carrier section 231 or 241 of the blade carrier 23 or 24 with respectively one enclosing section 50.1 or 51.2, that the stiffening rings 50 and 51 directly adjoin each other with their enclosing sections 50.1 and 51.2. Consequently, the stiffening rings 50 and 51 that are provided on both sides of the connection area 231 or 241 and that are respectively supported at the respective connection area 231 or 241 in a form-fit manner directly abut each other and the stiffening structure 5a or 5b thus created extends through the entire passage hole O1 or O2.

(17) The stiffening structure 5a or 5b with the stiffening rings 50 and 51, which are arranged at face sides of the blade carrier 23 or 24 that are facing away from each other, mainly receives radially acting forces. But at the same time, a simpler mounting as well as a simpler radial securing of the stiffening rings 50 and 51 to be mounted at the blade carrier 23 or 24 is facilitated as a result of the circumferential profile of the connection area 231 or 241.

(18) In a firtree-shaped cross sectional profile according to the variants of FIGS. 2A and 2B, the connection area 231, which is shown here by way of example, forms pairs of projections 2310.1/2310.2, 2311.1/2311.2 and 2312.1/2312.2 which axially extend in opposite directions. Each of these axial projections 2310.1 to 2312.2 protrudes in a ring-shaped manner at a face side of the carrier section 230. For forming the firtree-shaped profile, the axial length of the individual axial projections 2310.1 to 2312.1 or 2310.2 to 2312.2 decreases on each face side in the radial direction, in the present case radially inwards. Accordingly, a pair of axial projections 2312.1/2312.2, that is located closest to the passage hole O1, [has] the smallest axial extension, and the pairs of axial projections 2311.1/2311.2 and 2310.1/2310.2 that are arranged further radially outwardly respectively protrude further axially.

(19) Provided at the individual stiffening rings 50 and 51 are grooves corresponding to the projections 2310.1 to 2312.1 or 2310.2 to 2312.2 of a face side, so that the stiffening ring 50 or 51 that is respectively attached at a face side encloses each projection 2310.1 to 2312.1 or 2310.2 to 2312.2 at the respective face side in a form-fit manner, and accordingly each projection 2310.1 to 2312.2 is respectively received between a radially further internally and a radially further externally positioned section of the respective stiffening ring 50 or 51. Through a form-fit connection between the blade carrier 23 and the stiffening rings 50 and 51 that is thus formed, radial loads as they occur during operation of the engine T are introduced into the stiffening structure 5a in a manner distributed across the firtree-shaped profile. In addition, the stiffening structure 5a is thus radially fixated at the carrier section 230 of the blade carrier 23 already by plugging on the stiffening rings 50, 51, without any additional fastening means.

(20) For axially fixating the two stiffening rings 50 and 51, at least one connection element is provided, which is not shown in any more detail in FIGS. 2A and 2B. Via such a connection element, the two stiffening rings 50 and 51 are additionally directly connected to each other, so that any undesired displacement in the axial direction, and in particular a separation of the stiffening rings 50 or 51 from the blade carrier 23, is avoided. Each stiffening ring 50 or 51 is also supported at the other stiffening ring 51 or 50 via the at least one connection element, whereby any displacement relative to the same is avoided.

(21) For instance, an individual connection element can be used. In one variant, this individual connection element can extend at the stiffening structure 5a circumferentially in a ring-shaped manner, or can extend at least across the larger part of a radially inner circumference of the stiffening structure 5a. Alternatively, multiple local connection elements can be provided for axial securing in a manner offset with respect to one another along the circumference.

(22) For instance, a connection element 6 can be formed with a U-shaped cross section, as is shown in FIG. 2C for the stiffening structure 5b, wherein such a connection element 6 can also be used in a stiffening structure 5a of FIGS. 2A and 2B. Such a connection element 6 is connected in a form-fit and/or force-fit manner to both stiffening rings 50 and 51 via two legs or edges 60, 61 of the connection element 6. For fixating the connection element 6 at the stiffening rings 50, 51 that are embodied so as to be symmetrical to each other, a narrow groove is provided in every edge or leg 60, 61 into which respectively one extension in the form of a circumferentially extending, axially projecting edge or nose of the respective stiffening rings 50, 51 meshes.

(23) In the cross sectional view, both stiffening rings 50 and 51 are received between the two legs or edges 60, 61 of the connection element 6. At that, a force can be applied to each of the stiffening rings 50, 51 via the two respectively radially extending edges or legs 60, 61 that engage at the face side, pressing the stiffening ring 50, 51 in the direction of the other stiffening ring 51 or 50. Thus, the connection element 6 acts as a tensioning part, that axially tensions the two stiffening rings 50 and 51 against each other.

(24) In contrast to the variants of FIGS. 2A and 2B, in the embodiment variant of FIG. 2C the connection area 241 is not provided with a firtree-shaped profile, but with a T-shaped profile. The connection area 241 of FIG. 2C thus has two projections 2410.1 and 2410.2 that axially project in opposite directions. Also in this variant, they are respectively enclosed in a form-fit manner by the corresponding stiffening ring 50 or 51 that is arranged at the respective face side.

(25) In the embodiment variants of FIGS. 2B and 2C, it is further provided that the respective MMC core 500 of a stiffening ring 50 or 51 extends below the inner edge of the carrier section 230 or 240 with at least one section 500.1 or 500.2 made of the metal matrix composite. In the variant of FIG. 2B, the MMC core has a substantially L-shaped cross section. In the variant of FIG. 2C, the MMC core 500 of each stiffening ring 50 or 51 is embodied with a C-shaped cross section. In the variant of FIG. 2A, the MMC core 500 is thus arranged only axially next to the connection area 231 and in particular next to the projections 2310.1 to 2312.2. In contrast to that, in the variant of FIG. 2B, the MMC core 500 is arranged axially next to the connection area 231 and at least partially below the connection area 231, and accordingly in particular next to the projections 2310.1 to 2312.2 and at least partially below the projections 2310.1 to 2312.2. Through the C-shaped cross section, also respectively one section 500.3 or 500.4 of the MMC core 500 is additionally arranged above a projection 2410.1 or 2410.2, and consequently an axial projection 2410.1 or 2410.2 of the respective frontal or rear face side is positioned between two sections 500.1/500.3 or 500.2/500.4 of metal matrix composite.

(26) In FIGS. 3A and 3B, two different variants of the blade carrier 23 of the rotor blade assembly group 2a are illustrated. In both variants, the blade carrier 23 has a firtree-shaped cross sectional profile extending in the circumferential direction at the connection area 231 for the stiffening structure 5a and its stiffening rings 50 and 51 that are to be attached thereto. While in the variant of FIG. 3A, the blade carrier 23 is embodied with rotor blades 20 that are formed integrally thereat, the blade carrier 23 of FIG. 3B has multiple fastening grooves 232 arranged circumferentially next to each other for blade roots 200 of the rotor blades 20 that are to be fixated thereat.

(27) Regarding a firtree-shaped profile of the connection area 231 of a blade carrier 23, it is further illustrated by way of example based on the cross sectional rendering of FIG. 4 which constructional parameters can be used, where necessary, to influence the connection between the blade carrier 23 and the stiffening rings 50, 51, and thus the force transmission into the stiffening structure 5a. For instance, in the present case, a radius Ra for a transitional area between a radially extending face surface of the carrier section 230 and a radially outermost projection 2310.1 of a face side is shown, based on the size of which the degree of concavity of the transitional areas is influenced.

(28) A geometry of the firtree-shaped profile can further be characterized by an angle taken by two tangents with respect to each other, which are respectively applied in across the sectional view along the central axis M at the ends of the axial projections 2310.1 to 2312.1 or 2310.2 to 2312.2 of a face side. The larger the angle , the larger the axial extension of the firtree-shaped profile and/or the larger the gradation in the axial extension between the projections 2310.1 to 2312.1 or 2310.2 to 2312.2 that are provided at a face side.

PARTS LIST

(29) 11 low-pressure compressor 12 high-pressure compressor 13 high-pressure turbine 14 medium-pressure turbine 15 low-pressure turbine 20, 21, 22 rotor blade 200, 210, 220 blade root 23, 24, 25 blade carrier 230, 240, 250 carrier section 231 connection area 2310.1, 2310.2, axial projection 2311.1, 2311.2, 2312.1, 2312.2 232 fastening groove 241 connection area 2410.1, 2410.2 axial projection 2a, 2b, 2c rotor blade assembly group 30, 31 guide vane 4.1, 4.2 flange connection 50, 51 stiffening ring (stiffening element) 50.1, 51.2 enclosing section 500 MMC core 500.1, 500.2, MMC section 500.3, 500.4 5a, 5b stiffening structure 6 tensioning part (connection element) 60, 61 face-side edge/leg A outlet B bypass channel BK combustion chamber section C outlet cone E inlet/intake F fan FC fan housing M central axis/rotational axis O1, O2 passage hole R entry direction Ra radius S rotor shaft T turbine engine (gas turbine engine) TT turbine V compressor angle