GB2462268A - A segment of an annular guide vane assembly comprising a cut-out with a seal block within - Google Patents

A segment of an annular guide vane assembly comprising a cut-out with a seal block within Download PDF

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Publication number
GB2462268A
GB2462268A GB0813893A GB0813893A GB2462268A GB 2462268 A GB2462268 A GB 2462268A GB 0813893 A GB0813893 A GB 0813893A GB 0813893 A GB0813893 A GB 0813893A GB 2462268 A GB2462268 A GB 2462268A
Authority
GB
United Kingdom
Prior art keywords
seal
recess
segment
seal block
block
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Withdrawn
Application number
GB0813893A
Other versions
GB0813893D0 (en
Inventor
Paul Jenkinson
Pete Mcginigal
Kevin Scott
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to GB0813893A priority Critical patent/GB2462268A/en
Publication of GB0813893D0 publication Critical patent/GB0813893D0/en
Publication of GB2462268A publication Critical patent/GB2462268A/en
Withdrawn legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A segment of an annular guide vane assembly of a gas turbine engine comprises a radially inner support construction 21, a radially outer support construction 23, and a plurality of guide vanes 25 extending between the supports, the radially outer support comprising axially spaced upstream 27 and downstream rails / bands 29, wherein the upstream support rail comprising a recess / cut-out / notch 35. Within the recess is fitted a seal block 41 having a cross-section transverse to the circumferential direction which is substantially the same as that of the corresponding part of the rail. The seal block or recess may be provided with a slot 39, 45 within which a seal strip 43 is located. The seal strip and block may be an integral unit which is of very similar dimension to, and fills, the recess. The recess serves to reduce thermal distortion / stresses, while the seal block and strip prevents the escape of cooling fluid circulating within the stator vanes.

Description

A segment of an annular guide vane assembly of a gas turbine engine This invention relates to a segment of an annular guide vane assembly of a gas turbine engine.
More particularly, the invention relates to such a segment comprising a radially inner support construction, a radially outer support construction, and a plurality of guide vanes that extend radially between the inner and outer support constructions.
In one known segment comprising four guide vanes, cooling air passes first to a channel in the outer support construction, then to the interior of the four vanes to cool the vanes, and then to a channel in the inner support construction. The channels in the inner and outer support constructions are closed by surrounding parts of the gas turbine engine that fit over the channels. The engagement between these parts and the support constructions must be such that the cooling air present in the channels does not leak to the engine gas path that passes through the guide vanes.
A further requirement of the known segment is that the support constructions themselves be strong enough to withstand the high pressures present in use of the engine, yet flexible enough to cope with variation in temperature gradients within the constructions that occurs in use of the engine. With regard to the flexibility, if the constructions are not sufficiently flexible then undue stress is placed on the guide vanes resulting in cracking of the vanes. This will now be described in greater detail with reference to Figs 1 and 2.
The annular guide vane assembly segment of Figs 1 and 2 comprises a radially inner support construction 1, a radially outer support construction 3, and four guide vanes 5a, 5b, 5c, 5d. that extend radially between the constructions 1, 3.
Referring to Fig 1, during start-up of the gas turbine engine, the gas-washed inward facing layers 7, 9 of the constructions 1 3 will heat up more quickly than the not-gas-washed outward facing layers 11, 13 of constructions 1, 3. The resulting temperature gradients between the gas-washed and not-gas-washed layers cause inner construction 1 to increases in curvature and outer construction 3 to straighten. The effect of this is to apply a tensile stress to guide vanes 5a, 5d, and a compressive stress tc vanes 5b, 5c, see the arrows on the vanes in Fig 1.
Referring to Fig 2, during shut-down of the engine, the gas-washed inward facing layers 7, 9 will cool down more quickly than the not-gas-washed outward facing layers 11, 13 (the gas-washed layers are directly exposed to the cool gas that passes during shut-down) . The resulting temperature gradients between the gas-washed and not-gas-washed layers cause inner construction 1 to straighten and outer construction 3 to increase in curvature. The effect of this is to apply a compressive stress to guide vanes 5a, 5d, and a tensile stress to vanes 5b, 5c, see the arrows on the vanes in Fig 2.
Cracking of guide vanes is caused by both tensile stress and compressive stress. It can be seen from Figs 1 and 2 that the greatest stress (which is predominantly tensile) is experienced by guide vanes 5a and Sd. Thus, cracking of vanes 5a, Sd is more likely than vanes 5b, Sc. A further contributory factor to the cracking of vanes is temperature.
For example, if vane 5d usually operates at a higher temperature than vane 5a, then vane 5d will be more likely to crack than vane 5a.
EP-A-1793088 discloses a segment of an annular guide vane assembly of a gas turbine engine. The segment comprises a radially inner support construction, a radially outer support construction, and two guide vanes that extend radially between the inner and outer support constructions. The radially outer support construction comprises axially spaced circumferentially extending upstream and downstream support rails. The upstream support rail has a recess that extends (i) across the rail (ii) along the rail and (iii) radially inwardly from the radially outer top of the rail. A specially configured plate is secured to the downstream side of the upstream support rail over the recess to reduce fluid leakage through the recess.
The recess in EP-A-l793088 is included for the purpose of reducing stress in the assembly segment. However, the effectiveness of the specially configured plate in EP-A- 1793088 is limited.
According to the present invention there is provided a segment of an annular guide vane assembly of a gas turbine engine, the segment comprising a radially inner support construction, a radially outer support construction, and a plurality of guide vanes that extend radially between the inner and outer support constructions, the radially outer support construction comprising axially spaced circumferentially extending upstream and downstream support rails, the upstream support rail having a recess that extends (i) across the rail (ii) along the rail and (iii) radially inwardly from the radially outer top of the rail, a seal block being fitted in the recess, the seal block having a cross-section transverse to the circumferential direction that is substantially the same as that of the corresponding part of the rail, in use of the segment the seal block assisting in preventing the passage of fluid through the recess.
In a segment according to the preceding paragraph, it is preferable that a seal slot is formed in the recess, that the segment further comprises a seal strip, and that the seal block is held in the recess by engagement of the seal strip within the seal slot.
In a segment according to the preceding paragraph, it is preferable that a seal slot is formed in the seal block, and the seal strip is fitted tc the seal block by engagement of the seal strip within the seal slot in the seal block.
In a segment according to the preceding paragraph but one, it is preferable that the seal block and seal strip are integral.
In a segment according to any one of the preceding four paragraphs, it is preferable that the seal block substantially completely fills the entire recess.
In a segment according to any one of the preceding four paragraphs but one, it is preferable that the seal block substantially completely fills only a radially outer top portion of the recess.
A segment according to any one of the preceding six paragraphs preferably comprises a plurality of recesses and associated seal blocks.
A segment according to the preceding paragraph preferably comprises two recesses and associated seal blocks.
A segment according to any one of the preceding eight paragraphs preferably comprises three or more guide vanes.
A segment according to the preceding paragraph preferably comprises four guide vanes.
The invention will now be described, by way of example, with reference to the accompanying drawings, in which: Fig 1, already referred to, illustrates the behaviour of an annular guide vane assembly segment during start-up of the gas turbine engine; Fig 2, already referred to, illustrates the behaviour of the annular guide vane assembly segment during shut-down of the gas turbine engine; Fig 3 is a perspective view of an annular guide vane assembly segment wherein two scallops of material have been removed; Fig 4 illustrates a seal block and seal strip combination for location in each of the two scalloped areas of the segment of Fig 3; Fig 5 illustrates the segment of Fig 3 containing two seal block and seal strip combinations; Fig 6 is a cross-section showing the sealing around a seal block and seal strip combination; Fig 7 illustrates a first alternative seal block and seal strip combination; and Fig 8 illustrates a second alternative seal block and seal strip combination, wherein the block and strip are integral.
The segment of Fig 3 comprises a radially inner support construction 21, a radially outer support construction 23, and four guide vanes 25 that extend radially between the inner and outer support constructions 21, 23. The radially outer support construction 23 comprises axially spaced circumferentially extending upstream and downstream support rails 27, 29. A circumferentially extending channel 31 is formed between the upstream and downstream support rails 27, 29. Cooling air is supplied to channel 31, passes to the interiors 33 of guide vanes 25 to cool the vanes, and leaves the vanes by way of a further channel (not shown) in radially inner construction 21.
Two scallops of material are removed from the upstream support rail 27 to create corresponding scalloped areas 35.
Three support ILugs 37 remain following the scaiLloping. Seal slots 39 are machined into the scalloped areas 35.
Each of scalloped areas 35 is resealed by means of a seal block and seal strip combination. Fig 4 shows this combination. Fig 4a shows the seal block 41, Fig 4b shows the seal strip 43, and Fig 4c shows the block with the strip fitted. The strip fits into a seal slot 45 formed in the block. Fig 5 shows the scalloped areas 35 resealed. A block/strip combination is fitted into each area 35 by placing the strip 43 of the combination into the seal slot 39 of the area 35.
Fig 6 is a cross-section through a seal block and seal strip combination 41, 43 taken transverse to the circumferential direction around the annular guide vane assembly. The cross-section shows the interrelationship between the combination 41, 43 and both (i) the upstream support rail 27 into which the combination is fitted, and (ii) a casing 47 that fits over the radially outer support construction 23. With regard to (ii), the seal block 41 seals against the radially inner and radially outer sides 42, 44 of a circumferentially extending groove 46 in casing 47.
The addition of the two block/strip combinations 41, 43 to outer support construction 23 increases the flexibility of the construction without compromising how well it seals.
Thus, a reduction in stress in the guide vane assembly segment is achieved without loss of sealing.
The seal strips 43 are dual purpose. They hold the seal blocks 41 in position. They also provide a seal to prevent cooling air in circumferentially extending channel 31 escaping to the engine gas path that passes through the guide vanes 25.
The seal blocks 41 provide the seal originally provided by the removed scallops of the circumferentially extending upstream support rail 27. The cross-section of the blocks 41 transverse to the circumferential direction is the same as that of the corresponding part of the rail 27. This ensures that the seal provided by the blocks closely approximates that provided by the rail prior to scalloping. The thermal endurance of the material comprising the blocks should be similar to that of the rail.
The fit of the seal blocks 41 and seal strips 43 within the scalloped areas 35 must have sufficient play that, when the radially outer support construction 23 flexes during start-up/shut-down of the gas turbine engine, the flexing is not compromised by the blocks/strips resulting in additional mechanical loading, i.e. the clearances between the blocks/strips and the upstream support rail 27 must be such as to allow uncompromised flexing of support construction 23.
In the first alternative seal block and seal strip combination shown in Fig 7, the seal block 51 has been reduced in size and the seal strip 53 increased in size.
The second alternative seal block and seal strip combination shown in Fig 8 is the same as the block/strip combination shown in Fig 4 with the exception that the block and strip are integral.

Claims (10)

  1. Claims: 1. A segment of an annular guide vane assembly of a gas turbine engine, the segment comprising a radially inner support construction, a radially outer support construction, and a plurality of guide vanes that extend radially between the inner and outer support constructions, the radially outer support construction comprising axially spaced circumferentially extending upstream and downstream support rails, the upstream support rail having a recess that extends (i) across the rail (ii) along the rail and (iii) radially inwardly from the radially outer top of the rail, a seal block being fitted in the recess, the seal block having a cross-section transverse to the circumferential direction that is substantially the same as that of the corresponding part of the rail, in use of the segment the seal block assisting in preventing the passage of fluid through the recess.
  2. 2. A segment according to claim 1 wherein a seal slot is formed in the recess, the segment further comprising a seal strip, the seal block being held in the recess by engagement of the seal strip within the seal slot.
  3. 3. A segment according to claim 2 wherein a seal slot is formed in the seal block, and the seal strip is fitted to the seal block by engagement of the seal strip within the seal slot in the seal block.
  4. 4. A segment according to claim 2 wherein the seal block and seal strip are integral.
    -10 -
  5. 5. A segment according to any one of the preceding claims wherein the seal block substantially completely fills the entire recess.
  6. 6. A segment according to any one of claims 1 to 4 wherein the seal block substantially completely fills only a radially outer top portion of the recess.
  7. 7. A segment according to any one of the preceding claims comprising a plurality of recesses and associated seal blocks.
  8. 8. A segment according to claim 7 comprising two recesses and associated seal blocks.
  9. 9. A segment according to any one of the preceding claims comprising three or more guide vanes.
  10. 10. A segment according to claim 9 comprising four guide vanes.
GB0813893A 2008-07-30 2008-07-30 A segment of an annular guide vane assembly comprising a cut-out with a seal block within Withdrawn GB2462268A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0813893A GB2462268A (en) 2008-07-30 2008-07-30 A segment of an annular guide vane assembly comprising a cut-out with a seal block within

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0813893A GB2462268A (en) 2008-07-30 2008-07-30 A segment of an annular guide vane assembly comprising a cut-out with a seal block within

Publications (2)

Publication Number Publication Date
GB0813893D0 GB0813893D0 (en) 2008-09-03
GB2462268A true GB2462268A (en) 2010-02-03

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013171407A1 (en) * 2012-05-16 2013-11-21 Snecma Turbomachine distributor and production method
EP2971585A4 (en) * 2013-03-15 2016-12-07 United Technologies Corp Gas turbine engine turbine vane rail seal
US20170211421A1 (en) * 2014-08-04 2017-07-27 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
EP3244020A3 (en) * 2016-05-06 2018-05-16 United Technologies Corporation Gas turbine engine having a vane assembly
US20200024952A1 (en) * 2017-09-12 2020-01-23 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly, turbine including vane assembly, and gasturbine including vane assembly
US10822980B2 (en) 2013-04-11 2020-11-03 Raytheon Technologies Corporation Gas turbine engine stress isolation scallop
FR3111162A1 (en) * 2020-06-04 2021-12-10 Safran Aircraft Engines Welding with sealing strip
EP3926145A1 (en) * 2020-06-16 2021-12-22 Toshiba Energy Systems & Solutions Corporation Turbine stator blade

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060013685A1 (en) * 2004-07-14 2006-01-19 Ellis Charles A Vane platform rail configuration for reduced airfoil stress
EP1793088A2 (en) * 2005-11-30 2007-06-06 General Electric Company Methods and apparatus for assembling gas turbine nozzles

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060013685A1 (en) * 2004-07-14 2006-01-19 Ellis Charles A Vane platform rail configuration for reduced airfoil stress
EP1793088A2 (en) * 2005-11-30 2007-06-06 General Electric Company Methods and apparatus for assembling gas turbine nozzles

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2990719A1 (en) * 2012-05-16 2013-11-22 Snecma TURBOMACHINE DISPENSER AND METHOD OF MANUFACTURE
GB2516397A (en) * 2012-05-16 2015-01-21 Snecma Turbomachine distributor and production method
GB2516397B (en) * 2012-05-16 2018-11-28 Snecma Turbomachine distributor and production method
WO2013171407A1 (en) * 2012-05-16 2013-11-21 Snecma Turbomachine distributor and production method
EP2971585A4 (en) * 2013-03-15 2016-12-07 United Technologies Corp Gas turbine engine turbine vane rail seal
EP2984291B1 (en) * 2013-04-11 2020-12-30 United Technologies Corporation Nozzle segment for a gas turbine engine
US10822980B2 (en) 2013-04-11 2020-11-03 Raytheon Technologies Corporation Gas turbine engine stress isolation scallop
US10724404B2 (en) 2014-08-04 2020-07-28 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
US20170211421A1 (en) * 2014-08-04 2017-07-27 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
EP3156604A4 (en) * 2014-08-04 2017-10-18 Mitsubishi Hitachi Power Systems, Ltd. Stator blade, gas turbine, split ring, method for modifying stator blade, and method for modifying split ring
US10385705B2 (en) 2016-05-06 2019-08-20 United Technologies Corporation Gas turbine engine having a vane assembly
EP3244020A3 (en) * 2016-05-06 2018-05-16 United Technologies Corporation Gas turbine engine having a vane assembly
US20200024952A1 (en) * 2017-09-12 2020-01-23 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly, turbine including vane assembly, and gasturbine including vane assembly
US10844723B2 (en) * 2017-09-12 2020-11-24 DOOSAN Heavy Industries Construction Co., LTD Vane assembly, turbine including vane assembly, and gasturbine including vane assembly
FR3111162A1 (en) * 2020-06-04 2021-12-10 Safran Aircraft Engines Welding with sealing strip
EP3926145A1 (en) * 2020-06-16 2021-12-22 Toshiba Energy Systems & Solutions Corporation Turbine stator blade
US11459900B2 (en) 2020-06-16 2022-10-04 Toshiba Energy Systems & Solutions Corporation Turbine stator blade

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