EP3405651A1 - Rotor einer gasturbine mit kühlluftführung - Google Patents
Rotor einer gasturbine mit kühlluftführungInfo
- Publication number
- EP3405651A1 EP3405651A1 EP17702587.1A EP17702587A EP3405651A1 EP 3405651 A1 EP3405651 A1 EP 3405651A1 EP 17702587 A EP17702587 A EP 17702587A EP 3405651 A1 EP3405651 A1 EP 3405651A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling air
- segments
- turbine
- compressor
- rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 182
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 2
- 230000035515 penetration Effects 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims 1
- 239000012720 thermal barrier coating Substances 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 4
- 238000007789 sealing Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
Definitions
- Rotor of a gas turbine with cooling air guide The invention relates to a rotor of a gas turbine having a compressor section, a middle section and a Turbi ⁇ nenabites, being able to be conveyed through the mid section to the turbine section of the compressor section of the cooling air.
- the generic rotor initially serves for use in a gas turbine.
- the rotor comprises a
- Compressor section a middle section and a turbine ⁇ section.
- the compressor section can be formed by a only peo ⁇ gen compressor segment, but there are two or more consecutive segments compressor. At the compressor segments several successive compressor blade rings are arranged. In this regard, it is irrelevant to ⁇ next, whether each individual compressor segment has a single compressor blade ring or whether several compressor blade rings angeord ⁇ net on a compressor segment or whether compressor segments are still present without a blade ring. At least several nachei ⁇ nander following compressor blade rings are required.
- the middle section can be formed by a single mid-segment. Also provided is the realization of the middle section by two or more consecutive middle segments.
- the middle segments have here ⁇ at an outer shell, which in the operation of the gas turbine in all rule, or at least in sections, surrounded by compressor discharge air.
- the turbine section can be formed in principle analogous to a single turbine segment gebil ⁇ det. Again, it is envisaged that two or more turbine segments will be used. At this several successive ⁇ turbine blade rings are arranged. Equal ⁇ if as in the compressor section, may also be provided in Turbi ⁇ nenabites that a single turbine blade ring is disposed on each individual turbine segment.
- At least one compressor segment has cooling air passages which enable cooling air extraction from a removal region between two compressor blade rings.
- At least a plurality of circumferentially distributed first cooling air passages are located in the middle segments of the middle section, which guide channels of first cooling air from the first cooling air duct
- at least the first turbine segment corresponding firstdelufthimnle on.
- first cooling air channels distributed in the same number are present on the circumference in the middle segments as well as in the first turbine segment.
- first cooling air passages are now used which extend from the compressor section through the central section to the turbine section.
- at least the last compressor segment as well as the middle segments and at least the first turbine segment have mutually corresponding first cooling air ducts.
- Compressor blade ring is arranged.
- the removal of the first cooling air takes place from a first removal region between two compressor blade rings, for example between the penultimate and the third last compressor blade ring. Above all, it is relevant that the first cooling air has a lower temperature compared to the final compressor air.
- the first cooling air is conveyed through the first cooling air ducts in the first turbine segment at least to the second and / or further to a subsequent turbine blade ring.
- the cooling air ducts of the means ⁇ segments each ginnen or sawn roughly in the region of the engagement means end.
- the first cooling air passages in the middle segments each extend at a first distance to the rotor axis, which corresponds approximately to a second distance of the engagement means to the rotor axis. This is the case if the difference between the first distance and the second distance is less than 25% of the second distance.
- the first cooling air ducts are arranged in at least two adjacent segments such that the first cooling air can flow directly from one segment to the next segment in the successive first cooling air ducts.
- the first cooling air ducts end at opposite end faces of the two segments, wherein the end faces at the position of the first cooling air ducts advantageously form only a small gap between them or abut each other particularly advantageously.
- the first cooling air ducts at least from the last compressor segment over the Mittelseg ⁇ elements across the first turbine segment each frontally opposite arranged.
- the middle segments in a particularly vorteilhaf ⁇ ter an inner shell, so that the middle section forms a kind of hollow shaft.
- the rotor has obvious advantageous at least one tie rod, which extends along the rotor and connects the segments together. In this case, it is almost irrelevant how the tie rod is arranged. Furthermore, it is initially irrelevant whether one or more tie rods are used. As a rule, however, a central tie rod is used. However, it is also conceivable to use a plurality of tie rods distributed around the axis of rotation.
- the engagement means are formed by a spur toothing.
- a Hirth toothing is used for this purpose.
- the middle segments are at least over that region in which the compressor discharge air is located outside the middle segments, when the middle segments, radially outside the engagement means, no longer have any function with a completely closed outer shell.
- the closed contour is true at least for a theoretical outer shell over or through the center segment radially outwardly of the engagement means.
- Compressor end air in the respective junction between ⁇ adjacent segments between the outer shell and the first cooling air ducts frontally disposed outer seal ⁇ have medium. How the seal is realized, initially irrelevant, not necessarily an absolutely tight connection erforder ⁇ Lich is. Rather, it is sufficient if it due to the existing pressure differences between the pressure in the first cooling air ducts and the pressure outside the outer shell, ie the compressor discharge, and between the pressure in the first cooling air ducts and the pressure within the inner shell only to one in terms of the effectiveness of Cooling negligible cross flow comes.
- Sealant for example, be formed by a gap seal and / or a tongue and groove connection and / or by a labyrinth seal.
- the first cooling air channels in the first means segments are arranged so that their distance from the engaging means is open ⁇ ringer than the radial width of the engaging means. It benefits in particular ⁇ here is immediately adjacent Anord ⁇ voltage of the first cooling air channels to the engagement means.
- the openings of the first cooling air ducts are arranged at least in sections directly at the engagement means. Insofar as the first cooling air channels intersect at least in sections the A ⁇ engagement means, it being also provided that begin and end the first cooling air channels within the engagement means.
- the openings of the cooling air ducts arranged at the end face between see outer engagement means and inner engagement means are arranged.
- the removal of the first cooling air from the compressor takes place in a first removal region, which is arranged upstream of the third last compressor blade ring.
- the removal of the first cooling air between the third last and the fourth last takes place in a first removal region, which is arranged upstream of the third last compressor blade ring.
- Compressor blade ring or between the fourth last and the fifth last compressor blade ring.
- Cooling air is guided on the first turbine blade ring to the second and / or a subsequent turbine blade ring for cooling the turbine blades arranged there.
- a further improvement in the cooling of the turbine show ⁇ feln is achieved when third cooling air can be conveyed from the compressor segments to the turbine segments in addition, this is managed separately from the first into the firstdeluftka ⁇ nälen cooling air flowing in the rotor. This can be done in a simple manner by cooling air from a previous compressor blade ring, that is, preceding from a decrease in the first cooling air
- Removal area passed into the center of the rotor and then at least partially within the cooling air guide forming inner shell, ie in the free space between the hollow shaft formed by the middle segments and the tie rod, can flow to the turbine segments to be fed to the turbine blades there.
- the front side is arranged between the segments inner sealing ⁇ means are present, which are the extent to between the first cooling air ducts and the inner shell of said center segments ⁇ organize. In this respect, reference may be made with regard to their advantageous implementation to the previous comments on the outer sealants.
- third cooling air ducts distributed in the circumference are located in the inner region of the corresponding segment , For example, a middle segment, are arranged, which form a sufficient free cross section for the third cooling air.
- the arrangement of the first cooling air channels in the harshest operating region of the center segments makes it advantageously Mög ⁇ friendliness, in the center segments separated circumferentially disposed second cooling air channels distributed provided.
- second cooling air can be conveyed separately from the first cooling air from the compressor section through the middle segments to the turbine section.
- analog second sealing means are used frontally on the middle segments, which in this case are to be arranged between the first cooling air ducts and the second cooling air ducts.
- the supply of the first cooling air to the second and / or a subsequent turbine blade ring enables the particularly advantageous cooling of the first turbine blade ring with compressor discharge air.
- the first turbine segment in the circumference distributed fourth cooling air channels which are arranged radially au ⁇ ßerraum the engagement means. These are to be executed ⁇ such that the fourth cooling air turbine the turbine Blades of the first turbine blade ring can be supplied.
- Removal range is removed at least one compressor blade ring upstream of the first removal area for the first cooling air.
- third cooling air from the third removal region traverses the adjacent compressor segment upstream in a particularly advantageous manner, radially inwardly through third cooling air channels.
- this advantageous cooling air duct can be provided both for the second cooling air and for the third cooling air.
- the second cooling air from the second removal region subsequently traverses the adjacent compressor segment upstream, radially inward, through second cooling air channels.
- Compressor blade ring which has no cooling air channels on ⁇ .
- the outer shell of at least one middle segment is formed by a thermal barrier coating. This can be done in a particularly advantageous manner to act a ceramic thermal barrier coating.
- a thermal barrier coating By Ver ⁇ application of a thermal barrier coating, the heating of With ⁇ telsegmentes by the higher, outside the outer shell is reduced before ⁇ lying temperature of the compressor discharge air so that the cooling of the center segment may be particularly effective effectively by the firstdeluftka ⁇ ducts. It is be ⁇ Sonders advantageous if all means segments are provided with an ent ⁇ speaking thermal barrier coating.
- the temperature in the middle segments can thus advantageously be reduced compared with the known solutions in the prior art.
- a rotor according to the invention now leads to the formation of an improved gas turbine according to the invention, which has a compressor, a combustion chamber and a turbine, by the use of a rotor according to the invention or an embodiment advantageous for this purpose.
- FIG. 1 shows a first exemplary embodiment of a rotor with compressor segments and turbine segments, on each of which a vane ring is arranged;
- Figure 2 shows another embodiment of a rotor in which two blade rings on each one
- Blade segment are arranged
- FIG. 3 shows a third embodiment of a rotor with optimized cooling air flow.
- a first embodiment of a rotor Ol according to the invention is sketched schematically.
- the compressor section 20 is formed which is 20 in this case by three compressor segments 21a, 21b and 21c, each of said compressor segments 21 each ⁇ wells comprises a compressor blade ring 22a, 22b and 22c.
- the middle section 30 which is also formed by a plurality of middle segments 31a, 31b and 31c.
- the turbine section 40 follows, which in this schematic example also comprises three turbine segments 41a, 41b, 41c.
- each turbine segment 41 likewise has a turbine blade ring 42a, 42b or 42c.
- a centrally arranged tie rod 05 is used to connect the individual segments 21, 31 and 41 to each other.
- To cool the turbine blades by using cooling air from the compressor section 20 is on the one hand in a known manner further cooling air along a cooling air guide 07 between the segments 21, 31, 41 on the one hand and the tie rod 05 on the other hand inside the inner shell 34 of the middle section 30 ge ⁇ leads.
- To bridge the support 06 on the tie rod 05 is a third cooling air channel 37 in the second middle segment 31 b near the inner shell, so that the other cooling air can flow around the support 06.
- cooling air channels 25, 35 and 45 are now inserted in the segments 21, 31, 41, through the 25, 35, 45 first cooling air from the compressor section 20 through the mid ⁇ section 30 to the turbine section 40 can flow.
- First cooling air can in this case taken from a region before the penultimate compressor blade ring 22b and flow through existing in the penultimate compressor segment 21b first cooling air channels 25b and through the last compressor segment 21a existing first cooling ⁇ air channels 25a to the center section.
- 25a in the compressor section are in the Middle segments 31 also first cooling air channels 35a, 35b and 35c, through which the first cooling air can be passed through the central section 30 to the turbine section 40.
- the first turbine segment 41a likewise has a first cooling air channel 45a, so that first cooling air can be supplied to the second turbine segment 41b and thus to the second turbine blade ring 42b.
- this embodiment has all the segments by withdrawing second cooling air passages 26, 36 and 46, so that second cooling air from a region before the penultimate before ⁇ turbine blade ring 22c separate from the first cooling air passage 25, 35, 45 and separated from the other
- Cooling air within the inner shell 34 through the middle segments 31 to the third turbine segment 41 c and the third turbine ⁇ nenschaufelkranz 42 c can be performed.
- FIG. 2 outlines a further exemplary embodiment of a rotor 02 according to the invention, wherein, in contrast to the previous embodiment, the penultimate compressor segment 61b is the penultimate one in an exemplary manner
- Compressor vane ring 22c carries.
- a turbine segment 81b is used, which 81b carries the second turbine blade ring 42b and the third turbine blade ring 42c.
- a first cooling air duct 65b ends in the region between the penultimate compressor blade ring 22b and the third last compressor blade ring 22c.
- the penultimate compressor segment 61b has a second cooling air channel 66, which 66 the supply of
- Compressor vane ring 22c allows.
- the supply of the ers ⁇ th cooling air through the first cooling air ducts 65, 75, 85 ER follows analogous to the previous example, the center section 70 by first cooling air ducts 75. These 75 are in contrast to the previous embodiment in a range between the engagement means 77 and the Outer shell 73 of the middle segments 71.
- the further course of the first cooling air through the turbine section 80 through the first Turbinenseg ⁇ ment 81 a and the second turbine segment 81 b is analogous to the previous example through the first cooling air ducts 85 a and 85 b.
- the supply of the second cooling air is analogous to prior ⁇ herigem example, by the second cooling air channels 66 in the letz- th and penultimate compressor segment 61a, 61b and through the second cooling air channels 76 in the center segments 71 and the second cooling air passage 86a in the first turbine segment 81a, as well as in the following by the second cooling air duct 86b in the second turbine segment 81b.
- FIG. 3 shows a further exemplary embodiment for a rotor 03 with an advantageous cooling air guidance.
- the analogue structure with the Verdichtabrough 120 comprising a plurality of Ver emphasizerseg- elements 121, the central portion 130 comprising a plurality of means ⁇ segments 131 and the turbine section 140, which comprises turbine segments 141.
- the compressor segments 121 each one Compressor blade ring 22 and the turbine segments 141 each have a turbine blade ring 42 is arranged.
- the rotor 03 has a tie rod 05 with two support 06 in contact with the middle segments 131 on.
- the cooling air guide 07 is located between the access 05 and the segments 121, 131, 141, with third cooling air channels 137b, 137c being provided in the middle segments 131b, 137c to bypass the support 06.
- third cooling air channels 137b, 137c being provided in the middle segments 131b, 137c to bypass the support 06.
- fourth cooling air channels 148 for guiding compressor end air to the first turbine blade ring 42a and in a
- Ring cavity behind the first turbine segment 141a present.
- first cooling air channels 125, 135, 145 for guiding first cooling air from the compression section 120 to the turbine section 140 can be seen.
- first cooling air channels 125, 135, 145 for guiding first cooling air from the compression section 120 to the turbine section 140 can be seen.
- Cooling air is taken from a first removal area between the third last compressor blade ring 22c and the fourth last compressor blade ring 22d. Accordingly, in the last three compressor segments 121a, 121b and 121c, there are first cooling air passages 125a, 125b 125c. It is provided that the first cooling air channels 125 c in the third last compressor segment 121 c from a ring cavity below the flow path diagonally upstream radially inwardly into the region of the engagement means 138 leads. From here on, pull through first cooling air ducts 125b, 125a, 135, 145a, the Segmen ⁇ te 121b, 121a, 131, 141a to the second turbine segment 141b.
- cooling air ducts 145b in a Ringka ⁇ tivity in front of the turbine segment 141b and on to the turbine blade ring 42b and in a ring cavity behind the Turbi ⁇ nensegment 141b. This allows a particularly vorteilhaf ⁇ te cooling of the turbine blades, in particular the second turbine blade ring 42b.
- the arrangement of third cooling air passages 127e in the compressor segment 121e is to recognize a compressor blade ring, ie in this case the fourth last compressor blade ring 22d, upstream.
- the third cooling air passage 127e leads opposite to ers ⁇ th cooling air passage 125c in the third-last compressor segment 121c upstream of a ring cavity below the flow path radially inwardly into a region radially inside the input engagement means before the fifth last compressor segment 121e. From here, the third cooling air can flow through the cooling air guide 07 to the turbine section 140. This results in the execution of the intervening fourth last
- Compressor segment 121d without cooling air channels.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP16158055.0A EP3214266A1 (de) | 2016-03-01 | 2016-03-01 | Rotor einer gasturbine mit kühlluftführung |
PCT/EP2017/051734 WO2017148630A1 (de) | 2016-03-01 | 2017-01-27 | Rotor einer gasturbine mit kühlluftführung |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3405651A1 true EP3405651A1 (de) | 2018-11-28 |
Family
ID=55453069
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16158055.0A Withdrawn EP3214266A1 (de) | 2016-03-01 | 2016-03-01 | Rotor einer gasturbine mit kühlluftführung |
EP17702587.1A Withdrawn EP3405651A1 (de) | 2016-03-01 | 2017-01-27 | Rotor einer gasturbine mit kühlluftführung |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16158055.0A Withdrawn EP3214266A1 (de) | 2016-03-01 | 2016-03-01 | Rotor einer gasturbine mit kühlluftführung |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP3214266A1 (de) |
WO (1) | WO2017148630A1 (de) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101744411B1 (ko) * | 2015-10-15 | 2017-06-20 | 두산중공업 주식회사 | 가스터빈의 냉각장치 |
KR101985097B1 (ko) * | 2017-10-13 | 2019-09-03 | 두산중공업 주식회사 | 가스 터빈 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE865773C (de) * | 1941-09-10 | 1953-02-05 | Daimler Benz Ag | Luftkuehlung fuer die Schaufeltraeger mehrstufiger Verdichter |
US2741454A (en) * | 1954-09-28 | 1956-04-10 | Clifford R Eppley | Elastic fluid machine |
JPH0629521B2 (ja) * | 1985-03-31 | 1994-04-20 | 株式会社東芝 | ガスタ−ビンロ−タの冷却装置 |
US5144794A (en) * | 1989-08-25 | 1992-09-08 | Hitachi, Ltd. | Gas turbine engine with cooling of turbine blades |
KR100389990B1 (ko) * | 1995-04-06 | 2003-11-17 | 가부시끼가이샤 히다치 세이사꾸쇼 | 가스터빈 |
US6837676B2 (en) * | 2002-09-11 | 2005-01-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
EP1577493A1 (de) | 2004-03-17 | 2005-09-21 | Siemens Aktiengesellschaft | Strömungsmaschine und Rotor für eine Strömungsmaschine |
ES2308081T3 (es) * | 2004-09-22 | 2008-12-01 | Siemens Aktiengesellschaft | Sistema de refrigeracion para una turbina de gas y procedimiento para refrigerar una turbina de gas. |
EP2586968B1 (de) * | 2011-10-28 | 2019-07-10 | United Technologies Corporation | Sekundärflussanordnung für einen geschlitzten Rotor |
US9032738B2 (en) * | 2012-04-25 | 2015-05-19 | Siemens Aktiengeselischaft | Gas turbine compressor with bleed path |
KR101509382B1 (ko) * | 2014-01-15 | 2015-04-07 | 두산중공업 주식회사 | 댐핑 클램프를 구비한 가스 터빈 |
-
2016
- 2016-03-01 EP EP16158055.0A patent/EP3214266A1/de not_active Withdrawn
-
2017
- 2017-01-27 WO PCT/EP2017/051734 patent/WO2017148630A1/de active Application Filing
- 2017-01-27 EP EP17702587.1A patent/EP3405651A1/de not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
WO2017148630A1 (de) | 2017-09-08 |
EP3214266A1 (de) | 2017-09-06 |
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