GB2380236A - Fastener having cooling passage - Google Patents

Fastener having cooling passage Download PDF

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Publication number
GB2380236A
GB2380236A GB0123504A GB0123504A GB2380236A GB 2380236 A GB2380236 A GB 2380236A GB 0123504 A GB0123504 A GB 0123504A GB 0123504 A GB0123504 A GB 0123504A GB 2380236 A GB2380236 A GB 2380236A
Authority
GB
United Kingdom
Prior art keywords
article
main part
wall
fastener
head
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.)
Granted
Application number
GB0123504A
Other versions
GB2380236B (en
GB0123504D0 (en
Inventor
Anthony Gordon Razzell
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB0123504A priority Critical patent/GB2380236B/en
Publication of GB0123504D0 publication Critical patent/GB0123504D0/en
Priority to US10/246,698 priority patent/US6718774B2/en
Publication of GB2380236A publication Critical patent/GB2380236A/en
Application granted granted Critical
Publication of GB2380236B publication Critical patent/GB2380236B/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
    • F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
    • F16B35/041—Specially-shaped shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
    • F16B5/0241—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread with the possibility for the connection to absorb deformation, e.g. thermal or vibrational

Abstract

A fastener (31) is disclosed for a first article, for example a tile (29), to a second article for example an outer wall (27) of a wall structure of a combustor (15) of a gas turbine engine (10). The fastener (31) comprises an elongate main part, which may be in the form of a bolt (34). The main part can extend through the first and second articles. The main part defines a cooling pathway (46) therethrough to allow the passage of a cooling gas through the main part.

Description

1 2380236
Fastener This invention relates to fasteners. More particularly but not exclusively, the invention relates to 5 fasteners for fastening wall elements to wall structures of gas turbine engine combustors.
The designers of gas turbine engine combustors are required to meet stringent emission targets. This means that the temperatures within the combustors will need to 10 increase, as cooling air is diverted to the inside of the combustor to control emissions.
The present combustors are formed with a tiled inner wall, but such tiles have a maximum temperature threshold of about ll50 C.
15 According to one aspect of this invention, there is provided a fastener for fastening a first article to a second article at least the first article being in an elevated temperature environment, the fastener comprising an elongate main part which can extend through the first 20 and second articles, wherein the main part defines a cooling pathway therethrough to allow the passage of a cooling gas through the main part.
Preferably, the cooling aperture extends lengthways through the said main part.
25 In the preferred embodiment, the main part comprises a shank and a head. The pathway may extend through the shank a-d through the head.
According to another aspect of this invention, there -- provided a fastener comprising a main part having a head 30 I-] a shank wherein a pathway is defined through the head and stank to allow the passage of a gas through the main . . - T'ne pathway may be in the form of an aperture a:: enc. ng through the main part.
35 We shank is preferably formed to cooperate with a er part to secure the second article to the main part.
The shank may be threaded and the further part may be a nut. Preferably, the main part comprises a bolt.
The preferred embodiment is particularly suitable for S use in fastening a first article which may be in the form of a main body of a wall element to a second article which may be in the form of wall of a gas turbine engine combustor. The main body may be in the form of a wall tile. The main body may be formed of a ceramic material.
10 Preferably the head can engage the first article which may be generally planar in configuration. The first article may be the main body of a wall element.
The head is preferably shaped to co operate with the first article to allow differential thermal expansion IS between the first article and the main part of the fastener. The head may be of a generally conical configuration and may taper outwardly from a shank. The taper of the head may vary depending upon the difference in thermal 20 expansion coefficients in the in plane and perpendicular directions in the first article. Where the first article has isotropic thermal expansion coefficients, the taper may be substantially 45 to the longitudinal axis of the shank.
Where the first article has at least one anisotropic 25 thermal expansion coefficients, the taper may curve inwards or outwards. The head preferably has an inner surface which, in use, faces inwardly of the combustor. The inner surface is preferably coated with a thermal barrier coating. 30 In another embodiment the section of the cooling pathway extending through the head is preferably angled relative to the section extending through the shank. In another embodiment, the cooling aperture extends generally parallel to, and preferably substantially coaxially with, IS the main longitudinal axis of the main part. The fastener preferably includes a spacer to space the first article
from the second article. The main part conveniently extends through the spacer.
The spacer may be in the form of a further nut threadably receivable on the shank. The fastener may 5 further include load spreading means arrangeable on the shank between said spacer and the first article. The load spreading means may comprise a washer.
According to another aspect of this invention there is provided a wall element for a wall structure of a gas 10 turbine engine, the wall element comprising a main body and a fastener as described in paragraphs four to fifteen above to fasten the main body to an outer wall of the combustor. The material from which the main body is formed may be 15 a ceramic material, for example a ceramic matrix composite.
An example of a suitable ceramic matrix composite is silicon carbide fibre/silicon carbide matrix composite other examples include alumina fibre/alumina matrix composites and mullite fibre/mullite matrix composites or 20 mixtures of the foregoing. Such a material may have a temperature limit of greater than 1200 . The main body preferably has an inner surface which, in use, faces inwardly of the combustor. The inner surface of the main body is preferably coated with a thermal barrier coating.
25 The main body of the wall element may define at least one aperture to receive the fastener therethrough. The aperture may have a conical side which may taper inwardly from an inner surface of the main body to an outer surface thereof. Preferably, the shape of the side of the aperture 30 corresponds to the shape of the head of the securing member. Advantageously, the head of the securing member, and the side wall of the aperture taper at substantially the same angle. This tapering of the head and the aperture rovides the advantage in the preferred embodiment that the 35 d- erential thermal expansion between the main body and me securing member is accommodated by the sliding of the
head against the wall of the recess.
According to another aspect of this invention there is provided a wall structure for a combustor of a gas turbine engine, the wall structure comprising inner and outer 5 walls, the inner wall comprising a plurality of wall elements as described in paragraphs sixteen to eighteen above. According to another aspect of this invention there is provided a combustor for a gas turbine engine including 10 radially inner and outer wall structures as described in paragraph nineteen above.
Embodiments of the invention will now be described by way of example only with reference to the accompanying drawings in which: 15 Fig. 1 is a schematic sectional view of the upper half of a gas turbine engine; Fig. 2 is a sectional side view of a combustor for use in a gas turbine engine shown in Fig. It Fig. 3 is a view along the lines III-III in Fig. 2i 20 Figs. and 5 are close-up of the region marked IV in Fig. 3 showing different embodiments of the bolts and Fig. 6 is a close-up of the region marked V in Fig. 4.
With reference to Fig. 1, a dusted fan gas turbine engine generally indicated at 10 has a principal axis X-X.
25 The engine 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, and intermediate pressure turbine 17, a low pressure turbine 18 and an 30 exhaust nozzle 19.
The gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is accelerated by the fan to produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second air flow 35 which provides propulsive thrust. The intermediate pressure compressor 13 compresses the air flow directed
into it before delivering that air to the high pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 5 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive, the high intermediate and low pressure turbine 16, 17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The 10 high, intermediate and low pressure turbines 16, 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 and the fan 12 by suitable interconnecting shafts.
Referring to Fig. 2, the combustor 15 is constituted 15 by an annular combustion chamber 20 having radially inner and outer wall structures 21 and 22 respectively. The combustion chamber 20 is secured to a casing 23 by a plurality of pins 24 (only one of which is shown). Fuel is directed into the combustion chamber 20 through a number of 20 fuel nozzles 25 located at the upstream end 26 of the combustion chamber 20. The fuel nozzles 25 are circumferentially spaced around the engine 10 and serve to spray fuel into air derived from the high pressure compressor 14. The resultant fuel/air mixture is then 25 combusted within the combustion chamber 20. The combustion process which takes place within the chamber 20 naturally generates a large amount of heat. It is necessary, therefore, to arrange that the inner and outer wall structures 21 and 22 are capable of withstanding the heat.
30 The radially inner and outer wall structures 21 and 22 each comprise an outer wall 27 and an inner wall 28. The inner wall 28 is made-up of a plurality of discrete wall elements, each comprising a main body 30 in the form of a tile 29 and a plurality of fasteners 31 to fasten the 35 respective tile 29 to the outer wall 27.
Referring to Fig. 3, there is shown a close-up of one
of the tiles 29, which is formed of a ceramic material for example a ceramic matrix composite, which may be a silicon carbide fibre/silicon carbide matrix composite.
The tile 29 defines a plurality of conical apertures 5 32. Each fastener 31 comprises a main part in the form of a bolt 34 which is received through a respective one of the apertures 32. Each bolt 34 also extends through the outer wall 27 via a respective one of a plurality of apertures 33 defined therein and is secured to the outer wall 27 by 10 first nuts 36 threadably received on the bolts 34.
A plurality of spacers in the form of a second nuts 38 are provided to space the tile 29 from the outer wall 27 and to secure the bolt 34 to the tile 29. A washer 39 (see Figs. 4 and 5) is provided between the second nuts 38 and 15 the tile 29 to spread the load applied to the tile 29 by the second nut 38. The washer 39 can be made of a material capable of withstanding high temperatures and which can deform plastically. An example of such a material is C263 or platinum. C263 provides the advantage of ageing in 20 situ, thereby increasing its resistance to creep. Platinum provides the advantage of very good oxidation resistance.
The bolts 34 extends through the second nuts 38 whereby the gap between the main body 30 of the tile 29 and the outer wall 27 allows desired air flow between the main body 30 of 25 the tile 29 and the outer wall 27.
Referring to Fig. 4, there is shown a close-up of the region marked IV in Fig. 3, which shows the bolt 34 in more detail. The bolt 34 comprises a conical head 40 and a threaded 30 shank 42. The conical head has a conical surface 41 and a planar base surface 48. The head 40 is shaped to be seated within the respective conical aperture 32 which has a corresponding conical surface 43. The surface 41 of the conical head 40 substantially wholly engages the conical 35 surface 43 of the conical aperture 32.
The conical surface 41 of the conical head 40, and
correspondingly, the conical surfaces 43 of the conical Apertures 32 are arranged at an angle to the main axis of the bolt 34 of about substantially 45 (see Fig. 6).
The provision of a conical head 40 on each of the 5 bolts 34 and a plurality of conical apertures 32 provides in the embodiments described herein with the advantage that it allows differential thermal expansion between the bolt 34, which is formed of a metallic material, for example, a metallic alloy such as Haynes 25 alloy or Mar-M002, and the 10 tile 29, which is formed of the ceramic matrix composite.
As shown in Fig. 6, on relative thermal expansion between the bolt 34 and the main body 30 of the tile 29, the conical surface 41 of the comical head 40 slides relative to the conical surface 43 of the conical aperture 32, as IS shown by the arrow A, thereby maintaining the bolt load on the main body 30 of the tile 29, thereby maintaining the main body 30 of the tile 29 secured in place.
When the or each bolt 34 is received through the respective aperture 32 of the main body 30, the shank 42 20 extends through one of the second nuts 38 and through an aperture 33 in the outer wall 27 and threadably receives thereon one of the first nuts 36. The aperture 33 is generally circular and has a greater diameter than the shank 42 of the bolt 34. This allows a degree of lateral 25 movement of the shank 42 relative to the outer wall 27.
The first nuts 36 are screwed onto the threaded shank -2 and tightened against the outer wall 27 to a sufficient torque that allows the degree of lateral movement of the shank 42 relative to the outer wall 27. This potential for 30 ateral movement compensates differential expansion between -he tile 29 and the outer wall 27.
The bolt 34 has a main longitudinal axis Y-Y, and a ool ng pathway in the form of a cooling aperture 46 extends through the bolt 34 generally wholly parallel to, 3S end Biaxially with, the axis Y-Y. The cooling aperture 46 -.l'ovs air, as indicated by the arrows B to flow from the
region outside the outer wall 27 through the bolt 34 via the cooling aperture 46 to the inside of the combustor 15, thereby cooling the bolt 34 and allowing it to withstand higher temperatures within the combustor.
5 The inner surface 44 of the tile 29 may be coated with a thermal barrier coating 47 for example zirconia, yttria stabilized zirconia, to allow the tile to withstand higher temperatures. Similarly, the inner face 48 of the bolt head 40 is also coated with a thermal barrier coating 49, 10 e.g. zirconia, yttria stabilised zirconia, to increase its temperature capability further.
A further embodiment is shown in Fig. 5 includes all the same features as Fig. 4, and these have been designated with the same reference numeral. In the embodiment shown 15 in Fig. 5, the main body 30 of the tile 29 defines a plurality of angled effusion holes 52 to provide cooling air over the inner surface of the tiles 29, as indicated by the arrows C. In this embodiment, the bolt 34 includes a head, which is designated 140 in Fig. 5 on the shank 42.
90 The head 140 is generally the same as the head 40 shown in Fig. 4, but differs in that the cooling aperture 46 includes a first section 46A extending through the shank 42, and a second section 46B extending through the head 140. The first section 46A extends generally parallel to, 25 and coaxially with, the main longitudinal axis x-x of the bolt 34. The second section 4 6B is angled through the head 140, to be parallel to the effusion holes 52 through the tile 29. In this way, the air passing through the cooling aperture 46 in the bolt 34, as indicated by the arrow B 30 flows in the same direction as air flowing through the effusion holes 52.
The provision of the cooling aperture 46 has the advantage, particularly in the embodiment shown in Fig. 4 that it can be shaped to receive a key thereby providing a 35 reaction force to the tightening of the nut 36 on the shank 42.
Whilst endeavouring in the foregoing specification to
draw attention to those features of the invention believed to be of particular importance it should be understood that the Applicant claims protection in respect of any 5 patentable feature or combination of features hereinbefore referred to and/or shown in the drawings whether or not particular emphasis has been placed thereon.

Claims (1)

  1. À CLAIMS
    1. A fastener for fastening a first article to a second article at least the first article being in an elevated 5 temperature environment, the fastener comprising an elongate main part which can extend through the first and second articles, wherein the main part defines a cooling pathway therethrough to allow the passage of a cooling gas through the main part.
    10 2. A fastener according to claim l wherein the cooling pathway extends lengthways through the said main part.
    3. A fastener according to claim l or 2 including a securing member to secure the main part to the second article. 15 4. A fastener according to claim l, 2 or 3 wherein the main part comprises a shank and a head, the pathway extending through the shank and through the head.
    5. A fastener according to claim 4 when dependent upon Claim 3 wherein the main part is in the form of a bolt and
    20 the securing member is in the form of a nut threadably receivable on the bolt.
    6. A fastener according to claim 4 or 5 wherein the head is shaped to cooperate with the first article to allow differential thermal expansion between the first article 25 and said main part.
    7. A fastener according to claim 6 wherein the head is of a generally conical configuration and tapers outwardly from a shank, the taper of the head varying depending upon the difference in thermal expansion coefficients in the in 30 plane and perpendicular directions in the first article.
    8. A fastener according to claim 7 wherein where the first article has isotropic thermal expansion coefficients, the taper is substantially 45 to the longitudinal axis of the shank, and where the first article has at least one 35 anisotropic thermal expansion coefficient, the taper curves inwards or outwards.
    À 9. A fastener according to claim 6, 7 or 8 wherein the head has an inner surface which, in use, faces the elevated temperature environment, the inner surface being coated with a thermal barrier coating.
    5 10. A fastener according to any of claims 4 to 9 wherein the main part has a main axis and the cooling pathway extends through the head and the shank generally parallel to the main axis.
    11. A fastener according to any of claims 4 to 9 wherein 10 the main part has a main axis and the cooling pathway has a first section extending through the shank generally parallel to the main axis and a second section extending through the head at an angle to the mains axis.
    12. A fastener according to any of claims 4 to 11 15 Including a spacer to space the first article from the second article, the main part extending through the spacer.
    23. A fastener according to claim 12 wherein the spacer is in the form of a nut receivable on the shank of the fastener. 20 14. A fastener according to claim 13 including load spreading means arrangeable between the spacer and the irst article to spread the load from the spacer onto the first article.
    15. A fastener according to claim 14 wherein the load 25 spreading means is in the form of a washer.
    - 6. A wall element for a wall structure of a gas turbine engine, the wall element comprising a main body and a fastener as claimed in any preceding claim to fasten the main body to an outer wall of a combustion chamber.
    30 -7. A wall element according to claim 16 wherein the -.,ate-ial from which the main body is formed is a ceramic :-.aterial. :8. A wall element according to claim 16 wherein the _er-.mic material is a ceramic material composite.
    35:Q. A wall according to claim 17 wherein the ceramic -.at-:x composite is selected from silicon carbide
    fibre/silicon carbide matrix composite, alumina fibre/aluminium matrix composite or mullite fibre/mullite matrix composite.
    20. A wall structure for a combustor of a gas turbine 5 engine, the wall structure comprising inner and outer walls, the inner wall comprising a plurality of wall elements as claimed in any of claims 15 to 19.
    21. A combustor for a gas turbine engine, the combustor comprising radially inner and outer wall structures as 10 claimed in claim 20.
    22. A fastener substantially as herein described with reference to Figs. 3, 4 and 6 of the accompany drawings.
    23. A wall element substantially as herein described with reference to Figs. 3, 4 and 6, of the accompanying 15 drawings.
    24. A wall element substantially as herein described with reference to Figs. 3, 5 and 6 of the accompanying drawing.
    25. Any novel subject matter or combination including novel subject matter disclosed herein, whether or not 20 within the scope of or relating to the same invention as any of the preceding claims.
GB0123504A 2001-09-29 2001-09-29 A wall structure for a combustion chamber of a gas turbine engine Expired - Lifetime GB2380236B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB0123504A GB2380236B (en) 2001-09-29 2001-09-29 A wall structure for a combustion chamber of a gas turbine engine
US10/246,698 US6718774B2 (en) 2001-09-29 2002-09-19 Fastener

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0123504A GB2380236B (en) 2001-09-29 2001-09-29 A wall structure for a combustion chamber of a gas turbine engine

Publications (3)

Publication Number Publication Date
GB0123504D0 GB0123504D0 (en) 2001-11-21
GB2380236A true GB2380236A (en) 2003-04-02
GB2380236B GB2380236B (en) 2005-01-19

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Family Applications (1)

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GB0123504A Expired - Lifetime GB2380236B (en) 2001-09-29 2001-09-29 A wall structure for a combustion chamber of a gas turbine engine

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US (1) US6718774B2 (en)
GB (1) GB2380236B (en)

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US6718774B2 (en) 2004-04-13

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