• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Gas turbine, with a compressor, in which air is compressible; with a burner having at least one combustion chamber to which the air compressed in the compressor can be supplied and in which in the presence of the compressed air, a fuel is combustible while heating the air; with a turbine, in which the heated air is relaxing; wherein the heated air from the respective combustion chamber of the burner of the turbine is supplied via a respective intermediate piece (24) which is fixed with a downstream end (25) on a turbine blade carrier (26) of the turbine; wherein the respective intermediate piece (24) at the downstream end (25) has at least one fastening element (27) with at least one threaded bore (28) having an internal thread; wherein the respective fastening element (27) of the respective intermediate piece (24) projects into a recess (29) of the turbine blade carrier (26) of the turbine; wherein the vane support (26) has at least one unthreaded through-groove (30) formed axially open at a portion facing the respective intermediate piece (24); wherein the respective fastening element (27) of the respective intermediate piece (24) via a respective holding element (31) with at least one unthreaded through hole and at least one of the respective through hole of the holding element (31), the respective passageway (30) of the guide vane carrier (26) and the respective threaded bore (28) of the respective fastening element (27) penetrating fastening screw (32) on the guide blade carrier (26) is mounted.
    公开号:CH712452A2
    申请号:CH00162/17
    申请日:2017-02-10
    公开日:2017-11-15
    发明作者:Aschenbruck Emil；El Masalme Jaman；Blaswich Michael
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    Description: [0001] The invention relates to a gas turbine.
    The basic structure of a gas turbine, such as an industrial gas turbine, the principle known to those skilled in the art. Thus, a gas turbine has, as essential components, a compressor, a burner having at least one combustion chamber and a turbine. In the compressor, an air flow is compressed, wherein the compressed in the compressor air flow of the or each combustion chamber of the gas turbine can be fed. In the or each combustion chamber of the gas turbine, a fuel is burned in the presence of the compressed air, whereby the air is heated. The heated air can be supplied from the or each combustion chamber of the turbine of the gas turbine, wherein in the turbine, the heated air is expanded. The performance of such a gas turbine then results from the difference of the output from the turbine and the power absorbed by the compressor. This difference is due to the energy input in the or each combustion chamber of the burner.
    As already stated, the heated air, starting from the respective combustion chamber of the turbine can be supplied, via a respective intermediate piece, which is also referred to as a transition piece. Then, when the gas turbine comprises a plurality of combustion chambers, the air of the turbine can be fed from each combustion chamber via an intermediate piece in each case. The respective intermediate piece is attached to a downstream end of a turbine blade carrier. In this case, at least one fastening screw extends in the radial direction of the intermediate piece through a corresponding bore of the guide blade carrier and a corresponding bore of the intermediate piece.
    The intermediate pieces or transition pieces, which serve the flow guidance starting from the respective combustion chamber in the direction of the turbine of the gas turbine, are subject during operation extreme loads from temperature, pressure and vibration. This has the consequence that the intermediate pieces or transition pieces usually have a lifetime which is shorter than the life of the remaining components of the gas turbine. Therefore, it is necessary to replace the intermediate pieces or transition pieces. This presents difficulties in gas turbines known from practice, namely such that the intermediate pieces or transition pieces can not be exchanged without major assembly work on the rest of the gas turbine.
    There is therefore a need for a gas turbine, in which transition pieces or intermediate pieces, which serve the flow guidance of the heated air, starting from the respective combustion chamber in the direction of the turbine, can be replaced with less installation effort.
    On this basis, the present invention seeks to provide a novel gas turbine. This object is achieved by a gas turbine according to claim 1. According to the invention, the respective intermediate piece has, at the downstream end, at least one fastening element with at least one bore having an internal thread. The respective fastening element of the respective intermediate piece protrudes into a respective recess of the guide blade carrier of the turbine, wherein the guide blade carrier has at least one threadless through-groove, which is formed axially open at a portion facing the respective intermediate piece. The respective fastening element of the respective intermediate piece is mounted on the guide blade carrier via a respective retaining element having at least one unthreaded through-bore and at least one fastening bore of the retaining element, the respective through-hole of the guide-blade carrier and the respective threaded bore of the respective fastening element.
    The above embodiment of the gas turbine, namely the attachment of the respective intermediate piece on the guide vane support of the turbine via the respective fastening element and the respective holding element and the or each fastening screw, which the respective threadless through hole of the respective holding element, the respective threadless passageway of the guide vane carrier and the respective threaded bore of the respective fastener penetrates, allows an exchange of the respective intermediate piece with little installation effort.
    By way of e.g. simply cutting through the respective fastening screw on a relative to the respective holding member projecting portion, the respective holding element can be removed even with clamping the fastening screw and the respective fastener to be removed in the axial direction of the guide blade carrier. An exchange of spacers or transition pieces can be done without further disassembly of the gas turbine.
    Preferably, the respective holding element engages behind the respective fastening element and the guide blade carrier in the axial direction of the respective intermediate piece or of the guide blade carrier. This allows a particularly advantageous attachment of the respective intermediate piece on the guide blade carrier.
    According to an advantageous development, the respective fastener engages the respective intermediate piece, in particular on a cam-like, in the radial direction of the respective intermediate piece extending projection of the respective intermediate piece about an axis of rotation tiltably articulated. Preferably, the respective axis of rotation extends tangentially to the circumferential direction of the respective intermediate piece. Hereby, a particularly advantageous attachment of the respective intermediate piece on the guide vane carrier is possible. The tiltable connection of the respective fastening element on the respective intermediate piece is of particular advantage here.
    According to an advantageous embodiment, a combustion chamber housing which has a recess for the male flame tube of the respective combustion chamber, a dimension, so that on the same the respective intermediate piece can be mounted on the turbine and disassembled from the turbine. As a result, the respective intermediate piece can be easily removed from the gas turbine in the axial direction without having to carry out a further disassembly on the gas turbine.
    Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
    Fig. 1 is a gas turbine in cross section;
    FIG. 2 is a perspective view of a detail of the gas turbine of FIG. 1; FIG.
    FIG. 3 shows the detail of the gas turbine of FIG. 2 with the holding element removed; FIG.
    Fig. 4 is a plan view of Fig. 3; and
    5 shows a perspective view of a further detail of the gas turbine of FIG. 1.
    The invention relates to a gas turbine. Fig. 1 shows an axial section through a gas turbine 10 in the region of a compressor 11, a turbine 12 and a burner having at least one combustion chamber, between the compressor 11 and the turbine 12 connected burner 13. From the compressor 11, a stator-side housing 14 and a rotor side Shaft 15 shown with multiple compressor stages. From the turbine 12, a stator-side housing 16 and a rotor-side shaft 17 are shown with multiple turbine stages. The rotor-side shaft 15 of the compressor 11 and the rotor-side shaft 17 of the turbine 12 are coupled together.
    Of the burner 13, a burner housing 18 is shown, which is connected between the stator-side housing 14 of the compressor 11 and the stator-side housing 16 of the turbine 12. Preferably, the burner housing 18 has a plurality of recesses 19, each recess 19 of the receptacle each serving at least one flame tube 20 of a respective combustion chamber 21. About the circumference of the burner housing 18, these recesses 19 are arranged for receiving the flame tubes 20, preferably in the circumferential direction uniformly distributed.
    The compressor 11 serves to compress an air stream. The compressed air flow leaves the compressor 11 via a diffuser 22 and passes through the diffuser 22 in an annular flow channel 23, which is provided by the burner housing 18.
    Starting from this annular flow channel 23 of the burner housing 18, the compressed air reaches the region of each combustion chamber 21 and thus in the region of each flame tube 20, wherein in the region of the respective combustion chamber 21, a fuel is burned and in this case the air is heated.
    The heated air is supplied starting from the respective combustion chamber 21 of the turbine 12, for which purpose intermediate pieces 24 serve. Starting from each combustion chamber 21, the heated air can be supplied via a respective intermediate piece 24 of the turbine 12 of the gas turbine 10.
    2 and 3 show perspective detail views of an intermediate piece 24, via which starting from a combustion chamber 21 heated air of the turbine 12 can be supplied, wherein the intermediate piece 24 shown in Fig. 2 and 3 at a downstream end 25 with a vane carrier 26 of the turbine 12 is connected. The present invention relates to details of the connection of such an intermediate piece 24 to the vane support 26 of the turbine 12.
    The intermediate piece 24 shown in Fig. 2 and 3 is fastened with its downstream end 25 via at least one fastening element 27 on the guide blade carrier 26 of the turbine 12, wherein the respective fastening element 27 has at least one bore 28 with an internal thread. Fig. 4 it can be seen that on the fastening element 27 shown two such threaded holes 28 are formed with internal thread.
    The respective fastening element 27 of the intermediate piece 24 shown in Fig. 2 and 3 projects in the axial direction into a respective recess 29 of the guide blade carrier 26 of the turbine 12, wherein the respective recess 29 is open in the axial direction and facing the respective intermediate piece 24. The guide blade carrier 26 has at least one threadless through groove 30, which is formed axially open at a portion facing the intermediate piece 24. 4 it can be seen that for the respective fastening element 27 on the guide blade carrier 26, two such threadless passage grooves 30 extending in the axial direction are formed.
    With the respective fastening element 27 and the guide blade carrier 26, a respective holding element 31 cooperates for fastening the intermediate piece 24 shown in FIGS. 2 and 3 on the guide blade carrier 26, which has at least one unthreaded through-bore. Each of these non-threaded through holes of the respective holding member 31 serves to receive and guide a respective fastening screw 32. The respective fastening screw 32 penetrates the respective threadless through hole of the retaining element 31, the respective threadless through groove 30 of the guide blade carrier 26 and the respective threaded bore 28 of the fastener 26. Fig 2, it can be seen that the respective retaining element 31 partially engages behind and / or embraces the respective fastening element 27 and the guide blade carrier 26 in the axial direction.
    The fixation of the respective intermediate piece 24 on the guide blade carrier 26 of the turbine 12 is thus effected by the interaction of at least one fastener 27 and a corresponding retaining element 31 with at least one fastening screw 32. The or each fastening screw 32 generates a force between the respective fastener 27 and the vane support 26, whereby a positive connection is formed. Furthermore, the fastening screws 31 and the respective retaining element 31 fix the respective fastening element 27 via a positive connection.
    The respective threaded bore 28 of the respective fastening element 27, the respective through-hole 30 of the guide blade carrier 26 and the respective non-threaded through hole of the respective holding member 31 are aligned in the radial direction, wherein the respective fastening element 27 seen in the radial direction between a radially inner portion of the intermediate piece 24 and the radially outer holding member 31 is positioned.
    In the illustrated, preferred embodiment, the guide vane support 26 is designed to be split, wherein the same has a first part 34 facing the respective intermediate piece 24 and a second part 33 facing away from the respective intermediate piece 24. In this case, the recess 29 of the guide blade carrier 26 is formed on the intermediate piece 24 facing part 34 of the guide blade carrier 26. Likewise, the unthreaded through grooves 30 are formed on this part 34 of the vane support 26.
    In the illustrated, preferred embodiment of the invention, the respective fastening element 27 engages on the intermediate piece 24 tiltably articulated about a rotation axis 35, wherein this axis of rotation 35 extends tangentially to the circumferential direction of the respective intermediate piece 24. The respective fastening element 27 engages via the respective axis of rotation 35 on a cam-like, extending in the radial direction projection 36 of the intermediate piece 24, wherein this projection 36 bears with an axial surface on an axial surface of the guide blade carrier 26.
    The respective fastening element 27 protrudes into the respective recess 29 of the guide blade carrier 26 in the axial direction in sections, wherein an insertion depth of the respective fastening element 27 is limited in this recess 29 of the guide blade carrier 26 by a radially outer projection 37 of the fastening element 27. As best seen in FIG. 2, the respective holding element 31 engages or engages behind this projection 37 of the fastening element 27 in the axial direction on one side.
    As best seen in FIGS. 2 and 3, the two parts 33 and 34 of the vane carrier 26 form internal grooves in which vanes are threaded with corresponding portions 38. The vanes 39 form a guide vane ring thereby serve to guide the flow of heated air from the intermediate piece 24 towards a blade ring of the turbine 12 adjoining the vane ring. The vanes 39 have flow inlet edges 40, flow outlet edges 41 and between themselves between the flow inlet edges 40 and Flow outlet edges 41 extending, the flow guide serving pressure sides and suction sides.
    To disassemble an intermediate piece 24, only one or each fastening screw 32 has to be loosened or, in the case of clamps thereof, severed at a radially outward edge in relation to the respective holding element 31. Then then the corresponding holding element 31 can be easily removed. Then then the respective intermediate piece 24 can be removed in the axial direction of the guide blade carrier 26, and thereby that the respective fastener 27 optionally together with the or each still in the fastener 27 stuck, severed fastening screw 32 in the axial direction from the respective through-hole 30 and recess 29 in the guide vane 26 is pulled out in the axial direction. It is not necessary to access the vane support 26 of the turbine 12.
    Further, it is proposed that the recesses 19 of the burner housing 18 in such a way that over the same, the spacers 24 can be mounted and dismounted, which implies that an inner diameter of the recesses 19 is greater than an outer diameter of the spacers 24. This makes it easy via the recesses 19 in the combustion chamber housing 18, a worn intermediate piece 24 is removed and a new intermediate piece 24 is positioned and mounted on the vane support 26.
    The above embodiment of the gas turbine 10, namely the attachment of the respective intermediate piece 24 to the guide blade carrier 26 of the turbine 12 via the respective fastening element 27 and the respective holding element 31 and the or each fastening screw 32, which the respective threadless through hole of the respective holding element 31st , the respective threadless through groove 30 of the guide blade carrier 26 and the respective threaded bore 28 of the respective fastening element 27 penetrates, allows an exchange of the respective intermediate piece 24 with little installation effort. Even if the or each fastening screw 32 should be defective, the respective intermediate piece 24 can be withdrawn from the guide blade carrier 26 of the turbine 12 in the axial direction in the direction of the burner 13 from the guide blade carrier 26 and removed via the correspondingly dimensioned recess 19 of the burner housing 18 to in the reverse direction, a new intermediate piece 24 to be mounted on the vane support 26. The fastening screws 32 are with their external threads exclusively with a fastening element 27 of the respective intermediate piece 24 in engagement. In the region of the guide blade carrier 26, the fastening screws 32 penetrate exclusively the axially open, threadless through grooves 30 and in the region of the respective holding element 31 the unthreaded through holes. The fastening screws 32 and retaining element 31 are accessible via closed mounting openings of the burner housing 18, Fig. 1 shows such closure of such a mounting opening.
    REFERENCE SIGNS LIST 10 gas turbine 11 compressor 12 turbine 13 burner 14 housing 15 shaft 16 housing 17 shaft 18 burner housing 19 recess 20 flame tube 21 combustion chamber 22 diffuser 23 flow channel 24 spacer 25 end 26 vane support 27 fastener 28 threaded bore 29 recess 30 through groove 31 retaining element 32 mounting screw 33 Part 34 Part 35 Rotary axis 36 Projection 37 Projection 38 Section 39 Guide vane 40 Flow inlet edge 41 Flow outlet edge 42 Closure
    权利要求:
    Claims (10)
    [1]
    claims
    A gas turbine (10) having a compressor (11) in which air is compressible; a burner (13) having at least one combustion chamber (21) to which the compressed air in the compressor (11) can be supplied and in which in the presence of the compressed air a fuel is combustible while heating the air; a turbine (12) in which the heated air is depressurable; wherein the heated air from the respective combustion chamber (21) of the burner (13) of the turbine (12) via a respective intermediate piece (24) can be fed, which with a downstream end (25) on a guide vane carrier (26) of the turbine (12 ) is attached; characterized in that the respective intermediate piece (24) at the downstream end (25) has at least one fastening element (27) with at least one threaded bore (28) having an internal thread; the respective fastening element (27) of the respective intermediate piece (24) projects into a recess (29) of the guide blade carrier (26) of the turbine (12), wherein the guide blade carrier (26) has at least one threadless through groove (30) attached to one of the respective Intermediate piece (24) facing portion is formed axially open; the respective fastening element (27) of the respective intermediate piece (24) via a respective holding element (31) with at least one unthreaded through hole and with at least one of the respective through hole of the holding element (31), the respective passage groove (30) of the guide vane carrier (26) and the respective threaded bore (28) of the respective fastening element (27) penetrating fastening screw (32) on the guide blade carrier (26) is mounted.
    [2]
    2. Gas turbine according to claim 1, characterized in that the respective holding element (31) engages behind the respective fastening element (27) and the guide blade carrier (26) in the axial direction of the respective intermediate piece (24).
    [3]
    3. Gas turbine according to claim 1 or 2, characterized in that the respective fastening element (27) on the respective intermediate piece (24) about a rotational axis (35) tiltably articulated engages.
    [4]
    4. Gas turbine according to claim 3, characterized in that the respective axis of rotation (36) extends tangentially to the circumferential direction of the respective intermediate piece (24).
    [5]
    5. Gas turbine according to claim 3 or 4, characterized in that the respective fastening element (31) via the rotational axis (35) on a cam-like projection (36) of the respective intermediate piece (24) engages.
    [6]
    6. Gas turbine according to claim 5, characterized in that the cam-like projection (36) extends in the radial direction of the respective intermediate piece (24) and bears with an axial surface on an axial surface of the guide blade carrier (26).
    [7]
    7. Gas turbine according to one of claims 1 to 6, characterized in that the respective threaded bore (28) of the respective fastening element (27), the respective passageway (30) of the guide vane carrier (26) and the respective through hole of the respective holding element (31) in Radial alignment.
    [8]
    8. Gas turbine according to one of claims 1 to 7, characterized in that the guide blade carrier (26) of the turbine (12) is designed divided and a the respective intermediate piece (24) facing part (34) and one of the respective intermediate piece (24) facing away Part (33), wherein the or each axially open groove (30) of the vane support (26) on the respective intermediate piece (24) facing part (34) of the vane support (26) is formed.
    [9]
    9. Gas turbine according to one of claims 1 to 8, characterized by a burner housing (18), which has a respective dimensioned recess (19) for a male flame tube (20) of the respective combustion chamber (21), so that via the respective intermediate piece ( 24) can be mounted on the turbine (12) and disassembled from the turbine (12).
    [10]
    10. Gas turbine according to one of claims 1 to 9, characterized in that the respective fastening element (27) of the respective intermediate piece (24) in the axially open and the respective intermediate piece (24) facing recess (29) of the Leitschaufelträgers (26) Turbine (12) projects in sections in the axial direction, wherein a projection (37) of the respective fastening element (27) limits the axial insertion depth of the respective fastening element (27) in the recess (29) of the guide blade carrier (26).
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    同族专利:
    公开号 | 公开日
    DE102016108461A1|2017-11-09|
    JP2017203618A|2017-11-16|
    JP6768564B2|2020-10-14|
    KR20170126402A|2017-11-17|
    KR102317807B1|2021-10-25|
    CH712452B1|2021-01-15|
    CN107420136A|2017-12-01|
    CN107420136B|2021-02-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    EP2692995B1|2012-07-30|2017-09-20|Ansaldo Energia IP UK Limited|Stationary gas turbine engine and method for performing maintenance work|
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    US10072514B2|2014-07-17|2018-09-11|Siemens Energy, Inc.|Method and apparatus for attaching a transition duct to a turbine section in a gas turbine engine|
    US9359955B2|2014-08-28|2016-06-07|Siemens Energy, Inc.|Apparatus and method incorporating a transition AFT support for a gas turbine engine|DE102020111200A1|2020-04-24|2021-10-28|Man Energy Solutions Se|Fastening device for the elastic suspension of a transition duct on a guide vane carrier of a gas turbine|
    法律状态:
    2018-11-30| PFA| Name/firm changed|Owner name: MAN ENERGY SOLUTIONS SE, DE Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102016108461.1A|DE102016108461A1|2016-05-09|2016-05-09|gas turbine|
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