EP0203431B2 - Impingement cooled transition duct - Google Patents

Impingement cooled transition duct Download PDF

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Publication number
EP0203431B2
EP0203431B2 EP19860106295 EP86106295A EP0203431B2 EP 0203431 B2 EP0203431 B2 EP 0203431B2 EP 19860106295 EP19860106295 EP 19860106295 EP 86106295 A EP86106295 A EP 86106295A EP 0203431 B2 EP0203431 B2 EP 0203431B2
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EP
European Patent Office
Prior art keywords
impingement
transition duct
air
apertures
combustor
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.)
Expired - Lifetime
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EP19860106295
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German (de)
English (en)
French (fr)
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EP0203431B1 (en
EP0203431A1 (en
Inventor
Lewis Berkley Davis, Jr.
Walter Walls Goodwin
Charles Even Steber
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General Electric Co
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General Electric Co
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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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to gas turbine engines and, more particularly, to apparatus for cooling a transition duct employed to conduct hot gasses from a combustor to a turbine stage of an advanced heavy duty gas turbine engine.
  • a large heavy duty gas turbine engine conventionally employs a plurality of cylindrical combustor stages operated in parallel to produce hot energetic gas for introduction into the first turbine stage of the engine.
  • the first turbine stage preferably receives the hot gas in the shape of an annulus.
  • a transition duct is disposed between each of the combustor stages and the first turbine stage to change the gas flow field exiting each combustor from a generally cylindrical shape to one which forms part of an annulus. The gas flow from all of the transition ducts thus produces the desired annular flow.
  • thermodynamic efficiency of which a heat engine is capable depends on the maximum temperature of its working fluid which, in the case of a gas turbine, is the hot gas exiting the combustor stages.
  • the maximum feasible temperature of the hot gas is limited by the operating temperature limit of the metal parts in contact with this hot gas, and on the ability to cool these parts below the hot gas temperature.
  • the task of cooling the transition duct of an advanced heavy duty gas turbine engine, which is the one addressed by the present invention, is difficult because currently known cooling methods are either inadequate, or carry unacceptable penalties.
  • the entire external surface of the transition duct is exposed to relatively cool air discharged from the compressor, which supplies the total air flow for the gas turbine.
  • the flow of air over the exterior of the transition duct to the combustor causes passive cooling.
  • Some portions of the exterior of the transition duct are relatively well cooled by passive cooling, but others are poorly cooled thereby.
  • the portions of the exterior of the transition duct that are most poorly cooled are generally in structurally weaker areas, which are also areas most highly heated by the hot gas therewithin.
  • the maximum combustor exit temperature must be limited by the maximum allowed metal temperature of the most pooly cooled areas of the transition duct.
  • Another cooling technique which has found use in cooling the exterior of the transition duct employs an impingement plate, baffle or sleeve disposed a short distance away from the transition duct outer surface.
  • the impingement sleeve contains an array of holes through which compressor discharge air passes to generate an array of air jets which impinge on and cool the outer surface of the transition duct.
  • U.S. Patent No. 3,652,181 discloses such an impingement cooled transition duct in which the impingement sleeve surrounds only a portion of the transition duct. After impacting the surface to be cooled, the spent impingement air flows in the space of constant width between the transition duct outer surface and the impingement sleeve, toward holes in the transition duct. The air passing through these holes of equal size mixes with, and reduces the hot gas temperature just ahead of, the root area of the turbine blades and thus helps reduce the metal temperature of this portion of the turbine blades. Depending upon the heat transfer rate from the hot gas and the maximum allowed metal temperature, this method can use less cooling air than film cooling to maintain acceptable metal temperatures, and can be used in combination with film cooling to further reduce metal temperature. However, even the combination of impingement and film cooling for a transition duct would require more cooling air than is available in an advanced heavy duty gas turbine.
  • impingement cooling of a combustion component can either consume a portion of the air flow allocated to the combustion process, or be performed in series with the combustor such that the air used to cool a combustion component is subsequently used in the combustion process. It is the series mode of cooling a transition duct which is addressed by the present invention.
  • the pressure drop of an impingement cooling system essentially is generated by two components. First, there is a pressure drop needed to accelerate the air through the impingement sleeve holes to create the jets which impinge on the surface to be cooled. The second is more subtle, and is largely ignored in other known impingement cooling applications.
  • the spent impingement air If the spent impingement air is to be used in the combustor, it must be collected and brought to the combustor. The collection naturally takes place between the impingement sleeve and the external surface of the transition ducts, and it will be seen that, as one moves towards the combustor, the air flow velocity must steadily increase as more air is collected. The second component of pressure drop occurs due to the requirement to reaccelerate each additional quantity of spent impingement air to the velocity of that air already moving towards the combustor.
  • the local magnitude of the heat transfer in an impingement cooling system is determined by a number of variables.
  • these variables include the cooling air properties, the local distance between the impingement sleeve and the transition duct surface, the hole size, spacing and array pattern, the impingement air jet velocity, and the velocity of air flowing perpendicular to the air jet such as, for example, air resulting from the collection of spent impingement air.
  • An air jet formed by an opening in an impingement plate must traverse the space separating the impingement plate from the surface to be cooled, and must impact the surface to be cooled with sufficient velocity and in sufficient volume to effect the desired cooling.
  • the analysis of such jet impingement is relatively simple when only a single jet is involved. However, when an array of jets is used, the impingement air flowing away after impingement from one jet, captured between the surface being cooled and the impingement plate, tends to produce a crossflow of air which interferes with the cooling action of other jets, particularly those downstream in the direction along which the impingement air must flow to exit the constraining space.
  • a crossflow of air passing through the space between an aperture and the surface to be cooled may prevent the aperture-produced air jet from reaching the surface to be cooled, or may reduce the effectiveness of any portion of the air jet which may reach the surface to be cooled.
  • the actual cooling effects of an array of jets is difficult to predict, and so may only be derived empirically.
  • the object underlying the invention is to provide an improved impingement cooled transition duct which overcomes the above drawbacks of the prior art and, in other words, ensures an efficient use of the cooling air and an increased thermal efficiency for an advanced heavy gas turbine engine.
  • the present invention is as claimed in claim 1.
  • the inventional solution permits tailoring the cooling distribution according to the transition duct design requirements with regard to the interplay of the variables which affect the heat transfer and the pressure drop such than an efficient cooling of the entire transition duct is achieved.
  • the spacing between the impingement sleeve and the transition duct is systematically increased in the downstream direction of the crossflow of the impingement air in order to reduce the crossflow air velocity and thereby reduce the pressure drop of the impingement cooling sleeve.
  • the aperture size and spacing in an impingement cooling sleeve and the spacing between the impingement sleeve and the transition duct surface are all systematically varied to minimize the pressure drop required for the impingement cooling, thereby maximizing the thermal efficiency of the gas turbine engine.
  • a further advantageous effect is achieved when openings or apertures in some portions of the impingement sleeve are larger than openings in other portions thereof thereby providing jets of higher massflow which may penetrate across larger gaps between the transition duct and the impingement sleeve, and through greater crossflow or air.
  • the spacing between these larger holes is preferably varied relative to the spacing of the smaller holes, to establish a desired impingement cooling intensity as required by the transition duct design.
  • the present invention provides impingement cooling for a transition duct in an advanced heavy duty gas turbine engine.
  • the transition duct is cooled by impingement jets formed by apertures in a sleeve spaced a distance from the surface to be cooled.
  • the sleeve is configured so as to duct spent impingement air towards the combustor, where it can be subsequently used for mixing with, and combustion of, the fuel, or for cooling of the combustor.
  • the distance between the impingement sleeve and the transition duct surface is varied to control the velocity of air crossflow from spent impingement air in order to minimize the pressure loss due to crossflow.
  • the distance between the impingement sleeve and the transition duct increases systematically towards the combustor as the quantity of spent impingement air increases to a maximum value at the intersection of the combustor and the transition duct.
  • the cross sectional areas of the apertures are varied to project impingement jets over the various distances and crossflow velocities. Generally, larger aperture areas are used with larger distances.
  • the combination of variations in distance, aperture size, and inter-aperture spacing is utilized to vary the impingement cooling intensity to compensate for the variable internal heat load and also to produce the desired temperature distribution over the surface of the transition duct according to design requirements. The aforementioned variations are optimized to minimize the air flow pressure drop ahead of the combustion system while achieving the required cooling intensity according to design requirements.
  • a further development is characterized by a flow sleeve surrounding the combustor, and a flared entry portion at an end of the flow sleeve overlapping the exit and forming an aerodynamic converging shape therebetween, a flow of air through the aerodynamic converging shape flowing toward the combustor being effective to reduce a pressure at the exit below a pressure in the plenum whereby a pressure drop across the impingement sleeve produces an impingement jet of air from each of the apertures directed toward the transition duct and at least one of the distance, the area and the spacing being varied over the impingement sleeve to control a cooling in the surface.
  • an aft support having a continuous wall affixed to a transition duct.
  • An impingement insert is inserted within the wall having a planar bottom spaced a distance from the enclosed surface.
  • a plurality of apertures in the planar bottom the apertures having an area, the apertures being spaced apart by a spacing, the enclosed surface preferably including at least one film cooling aperture through the transition duct for exhausting spent impingement cooling air from between the impingement insert and the enclosed surface and the area and the spacing of the apertures being varied over the planar bottom in accordance with the distance between the planar bottom and the surface of the transition duct to tailor a cooling in the surface.
  • Fig. 1 is a simplified view, partially in cross section, of a combustor and a transition duct employing cooling according to the prior art.
  • Fig. 2 is a cross section of a plate to be cooled and an impingement plate to which reference will be made in describing the effect of air crossflow on the performance of impingement jets.
  • Fig. 3A is a simplified view, partially in cross section, of a combustor and a transition duct employing impingement cooling according to an embodiment of the invention.
  • Fig. 3B is a simplified view, partially in cross section, of a combustor and a transition duct employing impingement cooling according to another embodiment of the invention.
  • Fig. 4 is an enlarged view of an exit portion of the flow volume of Fig. 3.
  • Fig. 5 is a cross section taken along V-V of Fig. 3.
  • Fig. 6 is a cross section taken along VI-VI of Fig. 5.
  • Fig. 7 is a cross section taken along VII-VII in Fig. 6.
  • Gas turbine engine 10 includes a plurality of combustors 12, only one of which is shown, uniformly disposed with respect to a longitudinal axis thereof. In one type of gas turbine engine 10, ten combustors 12 are employed. Fuel and primary combustion air are injected into combustor 12 through a fuel nozzle 14. The fuel and air, ignited by a spark plug 16, burn within combustor 12. The hot products of combustion and heated excess air pass through a transition duct 18 to the inlet end of a turbine stage 20.
  • Combustor 12 and transition duct 18 are contained within a plenum 22 to which. a supply of compressed air is fed from a compressor outlet 24 of gas turbine engine 10. Compressed air from compressor outlet 24 flows along the surface of combustor 12 where it is admitted to the interior of combustor 12 through conventional apertures (not shown) in the surface thereof. The air thus admitted to the interior of combustor 12 enters into the combustion reaction downstream of fuel nozzle 14 or may be directed as a cooling film along the inner surface of combustor 12. Some compressed air may also be employed for diluting the hot gas to control and profile the temperature of the effluent of combustor 12. A flow sleeve 26 may be provided surrounding combustor 12 for improving the flow of air along the walls thereof.
  • transition duct 18 The outside surface of transition duct 18 is convectively cooled by compressed air flowing from the compressor outlet 24 toward combustor 12.
  • a radially inner surface 28 of transition duct 18 is disposed in the direct flow of compressed air as it changes direction after exiting compressor outlet 24.
  • a portion 30 of radially inner surface 28 nearer a combustor end 32 of transition duct 18 is more than adequately cooled.
  • a portion 34 of radially inner surface 28 nearer a turbine end 36 is cooled less strongly.
  • a radially outer surface 38 of transition duct 18 is protected from the direct flow of compressed air from compressor outlet 24.
  • a portion 40 of radially outer surface 38 nearer combustor end 32 is cooled by compressed air flowing about the circumference of transition duct 18 on its way to combustor 12. Such cooling is substantially less effective than that experienced by radially inner surface 28.
  • a portion 42 of radially outer surface 38 nearer turbine end 36 is most poorly cooled since very little compressed air circulates therepast. Thus, the cooling effectiveness on transition duct 18 tends to decrease from combustor end 32 to turbine end 36.
  • the cooling problem on portion 42 is additionally complicated by the fact that the hot gas flowing within transition duct 18 is strongly turned in this region. Thus, highly effective convective heat transfer from the hot gas operates on portion 42.
  • portion 42 becomes the hottest part of transition duct 18 and provides the effective limit on the temperature of the hot gas which can be admitted thereto from combustor 12.
  • the resulting unequal temperatures on transition duct 18 may set up troublesome thermal expansion patterns and possibly cause premature failure of transition duct 18.
  • portions 34 and 42 near turbine end 36 of transition duct 18 are less robust than are portions 30 and 40 near the combustor end 32, and are thus less capable of withstanding higher temperatures. At least part of this reduction in robustness ensues from the connection of an aft support 44 to portion 42.
  • the temperatures of portions 30 and 40 should be approximately equal and may be permitted to rise substantially higher than the temperatures of portions 34 and 42.
  • the temperatures of portions 34 and 42 should be approximately equal.
  • FIG. 2 there is shown a plate 46 whose surface is to be cooled by impingement cooling.
  • An impingement plate 48 spaced from the surface of plate 46, is pierced by a plurality of holes 50, 52 and 54.
  • a closed end 56 bridges plate 46 and impingement plate 48 forms a chamber 58.
  • An exit 60 in chamber 58 provides the only opening through which all air injected through holes 50, 52 and 54 must exit.
  • impingement plate 48 a pressure drop across impingement plate 48 is effective to produce air jets flowing through holes 50, 52 and 54.
  • Hole 50 being closest to closed end 56, forms an impingement jet which impinges on plate 46.
  • the air from hole 50 After impinging on plate 46, the air from hole 50 must flow toward exit 60 as indicated by an air flow arrow 62.
  • Air in the impingement jet formed by hole 52 whose flow is indicated by an air flow arrow 64, must penetrate the crossflow created by the air injected by hole 50. Assuming that the volumes of air injected into chamber 58 by holes 50 and 52 are equal, then the volume of air formed in the combined air flows from holes 50 and 52 is twice the volume from hole 50 alone.
  • the combined air flow downstream of hole 52 has twice the volume and twice the velocity of the crossflow air in air flow arrow 62 arriving at hole 52.
  • This combined volume forms the crossflow through which hole 54 must project its jet upon plate 46.
  • the total air passing downstream of hole 54 has thrice the velocity of that upstream of hole 52.
  • the embodiment of the invention shown in Fig. 3A permits tailoring the cooling to produce a desired temperature pattern on transition duct 18.
  • An impingement sleeve 66 surrounding, and spaced from, transition duct 18 forms a flow volume 68 therebetween which is substantially sealed at turbine end 36 and is open at combustor end 32 thereof.
  • Impingement sleeve 66 is pierced by a plurality of apertures 70 for training a plurality of impingement jets which impinge upon transition duct 18. As explained in the foregoing, since the spent impingement air must all flow toward an exit 72 at combustor end 32, its massflow must increase systematically toward exit 72.
  • the overall pressure drop across the impingement sleeve or the difference between the pressure in plenum 22 (the compressor discharge pressure) and that at exit 72 of flow volume 68. For example, it may be desirable to limit this pressure drop to less than two percent of the compressor discharge pressure.
  • the overall pressure drop through impingement sleeve 66 results from the accumulation of the pressure drop across apertures 70 and the pressure required to accelerate the spent impingement air up to the crossflow velocity in flow volume 68.
  • the velocity of a gas flowing in an enclosed channel varies inversely as the cross-sectional area of the channel.
  • the height of flow volume 68 increases from turbine end 36 to combustor end 32. This tends to reduce the air flow velocity near exit 72 compared to the velocity the air would attain if the smaller height of flow volume 68 were continued throughout its length. This permits taking advantage of a small height of flow volume 68 near turbine end 36 where the crossflow mass flow rate is small, while still limiting the velocity of the cross flow nearer exit 72.
  • the apertures 70 in the first band of apertures about impingement sleeve 66 adjacent turbine end 36 are shown much more closely spaced than are those in the last band of apertures 70 adjacent exit 72. Also, the spacing between the first two bands of apertures at turbine end 36 is much smaller than the spacing between the last two bands of apertures adjacent exit 72. Systematic variation in hole-to-hole and band-to-band spacing is seen at intermediate points.
  • apertures 70' in flow sleeve 26 permit that portion of the combustor air flow which does not pass through impingement sleeve 66 to combine with the impingement air flow spent prior to commencing combustion.
  • the number, size and distribution of apertures 70' are selected to permit the desired airflow, and create the required overall pressure drop for the impingement sleeve.
  • a seal 73 between flow sleeve 26 and impingement sleeve 66 permits considerable misalignment therebetween while preventing air flow from entering at their junction. Such entry would imbalance the air flow split between them.
  • FIG. 3B An alternate embodiment of the invention shown in Fig. 3B is quite similar to that shown in Fig. 3A. The principal difference is in the configuration of flow sleeve 26 and the junction between exit end 32 of impingement sleeve 66 and flared entry portion 74 of flow sleeve 26. An enlarged view of this junction is shown in Fig. 4, in which exit 72 is surrounded by a flared entry portion 74 of flow sleeve 26, creating an annular flow passage 78. Annular flow passage 78 takes the place of apertures 70' (Fig. 3A) having an area calculated to permit the required air flow to pass while creating the required overall pressure drop for impingement sleeve 66.
  • This embodiment requires precise control of the size of annular flow passage 78 in order to achieve consistent flow split and pressure drop performance among ten or more combustors operating in parallel, as is the case in a conventional or advanced heavy duty gas turbine engine.
  • aft support 44 includes a generally circular wall 80 welded at substantially its entire perimeter to transition duct 18 and extending through a circular opening 82 in impingement sleeve 66, thus forming a blind cup-shaped volume 84 which is open to plenum 22 at its upper end but which is substantially closed at the lower end.
  • a complete disclosure of the structure and function of aft support 44 is contained in U.S. Patent No. 4,422,288 whose disclosure is incorporated herein by reference.
  • transition duct 18 is curved outward toward cup-shaped volume 84 in this cross section.
  • the following disclosed technique for providing cooling to the portion of transition duct 18 which is enclosed with circular wall 80 provides an excellent example of the power and flexibility for tailoring the impingement cooling of a surface over which differences in heat load, distance and air cross-flow volume are all encountered.
  • An impingement insert 86 having an upward-directed wall 90 and a planar bottom 92 is tightly fitted into cup-shaped volume 84 with planar bottom 92 spaced from the surface of transition duct 18.
  • Upward-directed wall 90 preferably includes a flange 94 at its upper extremity for attachment to the inner surface of circular wall 80.
  • Flange 94 is preferably attached to circular wall 80 using, for example, welding.
  • An annular space 96 between upward-directed wall 90 and circular wall 80 permits insert 86 and wall 90 to reach the same temperature before they are joined at flange 94 thus minimizing the thermal stress at this joint.
  • a plurality of apertures 98 in planar bottom 92 permit the pressurized air in plenum 22 to form impingement jets for cooling an enclosed surface 100 of transition duct 18 within circular wall 80.
  • film cooling apertures 102 are disposed in two staggered rows 104 and 106 located near the upstream edge of planar bottom 92 with respect to the gas flow within transition duct 18. As best illustrated in Fig. 6, film cooling apertures 102 are inclined in the direction of gas flow thereby encouraging film cooling of the inner surface of transition duct 18 by the air passing therethrough. Such film cooling strongly modifies the local heat load downstream of film cooling apertures 102.
  • Apertures 98 are arranged in nine rows 108-124, each aligned transverse to the gas-flow path.
  • the three apertures 98 closest to the center of each of rows 114, 116 and 118 are of relatively small diameter. This smallness is in response to two factors, 1) this region of enclosed surface 100 is strongly film cooled by film cooling apertures 102, and 2) planar bottom 92 and enclosed surface 100 are spaced relatively close together, as seen in the cross section through row 116 in Fig. 5.
  • the outer three apertures 98 in rows 114, 116 and 118 become progressively larger in response to the increasing distance over which the impingement jets must be projected (see Fig. 5).
  • Rows 108 and 124 contain apertures 98 of intermediate size and closest spacing. This is in response to the combination of the shorter distance between planar bottom 92 and enclosed surface 100 in these locations (see Fig. 6) as well as the fact that there are no upstream impingement jets to produce a crossflow to interfere with the projection of cooling air upon enclosed surface 100.
  • Row 110 and 122 contain apertures 98 of larger size and wider spacing to compensate for the presence of crossflow from upstream impingement jets as well as the increasing distance (see Fig. 6).
  • the present invention is capable of tailoring the cooling provided by impingement jet cooling over an area where the three variables of heat load, distance and air crossflow are present in independent fields over the areas of interest.
  • air crossflow velocity is controlled by purposely increasing the distance between transition duct 18 and impingement sleeve 66 and compensating for the increased distance by increasing the diameters of apertures 70.
  • the spacing of the larger-diameter apertures 70 is increased to control the air mass flow density.
  • the distance is generally fixed by the design of transition duct 18.
  • the varying distances are accommodated by suitably controlling the diameter and spacing of apertures 98. Additionally, the problem of disposing of the spent impingement air is solved by employing the spent impingement air for film cooling and by further modifying the diameter and spacing of apertures 98 to compensate for the resulting variation in the heat load over enclosed surface 100.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Devices That Are Associated With Refrigeration Equipment (AREA)
  • Heat Treatments In General, Especially Conveying And Cooling (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
EP19860106295 1985-05-14 1986-05-07 Impingement cooled transition duct Expired - Lifetime EP0203431B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US73401885A 1985-05-14 1985-05-14
US734018 1985-05-14

Publications (3)

Publication Number Publication Date
EP0203431A1 EP0203431A1 (en) 1986-12-03
EP0203431B1 EP0203431B1 (en) 1990-11-22
EP0203431B2 true EP0203431B2 (en) 1996-05-22

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EP19860106295 Expired - Lifetime EP0203431B2 (en) 1985-05-14 1986-05-07 Impingement cooled transition duct

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EP (1) EP0203431B2 (enrdf_load_stackoverflow)
JP (1) JPS629157A (enrdf_load_stackoverflow)
AU (1) AU593551B2 (enrdf_load_stackoverflow)
CA (1) CA1263243A (enrdf_load_stackoverflow)
DE (1) DE3675690D1 (enrdf_load_stackoverflow)
NO (1) NO162887C (enrdf_load_stackoverflow)

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CA1263243A (en) 1989-11-28
NO861900L (no) 1986-11-17
EP0203431B1 (en) 1990-11-22
AU5735386A (en) 1986-11-20
EP0203431A1 (en) 1986-12-03
NO162887B (no) 1989-11-20
AU593551B2 (en) 1990-02-15
DE3675690D1 (de) 1991-01-03
NO162887C (no) 1990-02-28
JPS629157A (ja) 1987-01-17
JPH0524337B2 (enrdf_load_stackoverflow) 1993-04-07

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