EP2665896A1 - Intermediate housing of a gas turbine with an outer bounding wall, having upstream of a supporting rib a contour that changes in the circumferential direction, for reducing secondary flow losses - Google Patents

Intermediate housing of a gas turbine with an outer bounding wall, having upstream of a supporting rib a contour that changes in the circumferential direction, for reducing secondary flow losses

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Publication number
EP2665896A1
EP2665896A1 EP12716196.6A EP12716196A EP2665896A1 EP 2665896 A1 EP2665896 A1 EP 2665896A1 EP 12716196 A EP12716196 A EP 12716196A EP 2665896 A1 EP2665896 A1 EP 2665896A1
Authority
EP
European Patent Office
Prior art keywords
boundary wall
intermediate housing
radially outer
circumferential direction
support ribs
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
EP12716196.6A
Other languages
German (de)
French (fr)
Other versions
EP2665896B1 (en
Inventor
Martin Hoeger
Inga Mahle
Jochen Gier
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2665896A1 publication Critical patent/EP2665896A1/en
Application granted granted Critical
Publication of EP2665896B1 publication Critical patent/EP2665896B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D25/14—Casings modified therefor
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the invention relates to an intermediate housing, in particular of turbines of a gas engine, according to the preamble of patent claim 1.
  • a multi-shaft turbomachine such as a multi-shaft gas engine has a plurality of compressor components, at least one combustion chamber and a plurality of turbine components.
  • a two-shaft gas engine has a low-pressure compressor, a high-pressure compressor, at least one combustion chamber, a high-pressure turbine and a low-pressure turbine.
  • a three-shaft gas engine has a low-pressure compressor, a medium-pressure compressor, a high-pressure compressor, at least one combustion chamber, a high-pressure turbine, a Mitteldmckturbine and a low-pressure turbine.
  • FIG. 1 shows a highly schematic section of a multi-shaft gas engine in the region of a rotor 10 of a high-pressure turbine 11 and a rotor 12 of a low-pressure turbine 13.
  • an intermediate housing 14 with a transition flow channel 33 extends to the flow, which leaves the high pressure turbine 11 to supply the low pressure turbine 13, wherein in the transitional flow channel 33 at least one support rib 15 is positioned.
  • the support rib 15 is a stator-side component, which carries the flow flowing through the transition flow channel 33.
  • a flow-guiding support rib 15 has a front edge 16, which is also referred to as a flow inlet edge, via a rear edge 17, which is also referred to as a flow outlet edge, and via side walls 18.
  • transition flow channel 33 can (see Fig. 1) upstream of the support ribs 15 in the region of an entry into the transitional flow channel 33 or in the region of a leading edge 34 of the intermediate housing 14 radially outwardly in the same open a cavity 19, through which a small amount of cooling air 21a, which deals with the high pressure
  • CONFIRMATION COPY turbine 11 leaving gas flow 20 mixed.
  • This cavity 19 is located between the NDT housing and the intermediate housing 14, which is sealed with a seal 21 c. Only a weak leakage flow 21b flows through this seal 21c, since the NDT housing and the intermediate housing 14 can not be firmly connected to each other.
  • the static pressure of the gas flow 20 in the area of entry into the cavity 19 is below the pressure of the cooling air 21b in the secondary air area 21d of the annulus.
  • FIG. 2 shows a dimensionless circumferential direction u / t, where t corresponds to the support rib pitch in the circumferential direction u.
  • the pressure fields of the pressure increase ⁇ on the circumferential position of the support ribs 1 and the pressure drop ⁇ at the circumferential position between adjacent support ribs 15 respectively upstream of the leading edges 16 of the support ribs 15 are shown in dashed lines in the cavity 19 so that Further, the pressure fluctuation of FIG. 2 in the cavity leads to a higher pressure gradient between the gas flow 20 and the cooling air flow 21b, which ultimately increases the leakage and degraded efficiency the turbomachine leads.
  • the present invention is based on the problem to provide an intermediate housing, by means of which the efficiency can be increased.
  • the radially outer boundary wall has a contour which changes in the circumferential direction at least in a section upstream of the support rib.
  • Prior art known turbomachine in the region of an intermediate housing and thus flow channel between two turbine components; 2 shows a detail of the arrangement of Figure 1 in the radial direction.
  • FIG. 3 is a highly schematic, fragmentary longitudinal section through a flow machine in the region of an intermediate housing according to the invention, which is positioned between two turbine components;
  • Fig. 4 is a diagram for illustrating the invention.
  • Fig. 5 is another diagram for illustrating the invention.
  • the present invention relates to the field of multi-shaft turbomachinery, in particular multi-shaft gas engines, with several compressor components and several turbine components.
  • the basic structure of such a turbomachine is familiar to the person skilled in the art and has already been described in connection with FIG.
  • the present invention now relates to details of an intermediate housing 14 of such a turbomachine, by means of which the entry of a guided in a sselluftströmungska- channel 19 cooling air flow can be improved in the guided by the transitional flow channel 33 of the intermediate housing 14 gas flow, namely in an inlet region of the transitional flow channel 33 upstream of in the transitional flow channel 33 positioned support ribs 15th
  • the invention is applicable both to an intermediate housing 14 of a twin-shaft turbomachine which extends between a high-pressure turbine 11 and a low-pressure turbine 13, and to an intermediate housing of a three-shaft turbomachine which extends between a high-pressure turbine and a medium-pressure turbine or between a medium-pressure turbine and a low-pressure turbine, used.
  • FIG. 3 shows a section of a turbomachine in the region of an intermediate housing 14, a transitional flow channel 33 of this intermediate housing 14 and a turbine component positioned upstream of the transitional flow channel 33, designed as a high-pressure turbine 11 in the exemplary embodiment shown.
  • FIG. 3 shows the cooling air flow channel 19 from the radially outward direction the transitional flow channel 33 opens, namely upstream of support ribs 15 which are positioned in the transitional flow channel 33.
  • the cooling air flow channel 19 is thereby limited in sections by the front edge 34 of the intermediate housing 14.
  • the transitional flow channel 33 is bounded radially inwardly by a stator-side boundary wall 23 and also radially on the outside by a stator-side boundary wall 24.
  • a boundary wall 25 of the high-pressure turbine 11 adjoins the rotor 10 of the high-pressure turbine 11 radially on the outside.
  • the radially outer boundary wall 24 of the transition flow channel 33 can be located at least in a section upstream of the support ribs 15 be provided with a circumferentially changing contour.
  • the radially outer boundary wall 24 of the transitional flow channel 33 at least in a transition section between the front edge 34 of the intermediate housing 14 and the transitional flow channel 33 has a circumferentially changing contour.
  • this circumferentially changing contour of the radially outer boundary wall 24 of the transition flow channel 33 can also extend into a region downstream of the leading edges 16 of the support ribs 15, FIG. 3 showing two contours formed at different circumferential positions u / t 24 and 24 'for the radially outer boundary wall of the transitional flow channel 33 shows.
  • the radially outer boundary wall 24 of the transition flow channel 33 has in the inlet region of the transition flow channel 33 upstream of the leading edges 16 of the support ribs 15 via a boundary wall section or boundary wall 26 with a minimum radius of curvature and thus maximum curvature.
  • the contour of the radially outer boundary wall 24 of the transition flow channel 33 changes in the circumferential direction, u or u / t such that an axial position (axial direction x) and / or a radial position (radial direction r) of the boundary wall section or boundary wall point 26 with minimal Radius of curvature in the circumferential direction u or ut changed.
  • both the axial position and the radial position of the boundary wall point 26 change with a minimum radius of curvature.
  • the axial position of the boundary wall 26 with minimal radius of curvature changes in the circumferential direction u or u / t such that approximately at the circumferential position of the leading edges 16 of the support ribs 15 this boundary wall 26 in the axial direction x maximum upstream and approximately in a circumferential position half pitch between two adjacent supporting ribs in the axial direction x offset or positioned downstream of maximum. Between these maximum upstream and downstream from axial positions, the axial position of the boundary wall point 26 changes continuously or continuously in the circumferential direction.
  • the radial position of the boundary wall 26 with minimal radius of curvature changes in the circumferential direction u or u / t such that approximately at the circumferential position of the leading edges 16 of the support ribs 15 of this boundary wall 26 in the radial direction r maximum radially outward and approximately in a circumferential position half pitch between two adjacent support ribs 15 in the radial direction r is offset or positioned maximally radially inward. Between these maximum radially inner and radially outer radial positions, the radial position of the boundary wall point 26 changes continuously or continuously in the circumferential direction.
  • FIG. 3 of the radially outer boundary wall of the transition flow channel 33 corresponds to the contour thereof approximately at the circumferential position of a front edge 16 of a support rib 1, whereas the contour shown in Fig. 3 24 'of the same contour approximately in a circumferential position Division between two adjacent support ribs 15 corresponds. Further details regarding the offset of the axial position and the radial position of the boundary wall point 26 with a minimum radius of curvature in the circumferential direction u or u / t are described below with reference to FIG. 4. In Fig. 4 is on the horizontal axis an absolute value ⁇ / X K S between the axial distance ⁇ (see Fig.
  • the region 28 of FIG. 4 visualizes a preferred range of validity for the ratio ⁇ / XKS and / or Ar / x ⁇ s changing in the circumferential direction u or ut and thus the offset of the axial position u and u / t changing in the circumferential direction u or u / t / or the radial position of the boundary wall 26 with a minimum radius of curvature.
  • the ratios Ax / x K s and ⁇ / XS are up to 40%.
  • the ratio changes in the circumferential direction u or u / t
  • the curve 29 within the range 28 visualizes the preferred circumferentially varying ratio AX / XS and thus the circumferentially varying offset of the axial position of the minimum crimp radius limiting wall point 26, where the offset of the axial position is in the range of half Division between two adjacent support ribs is the largest and the ratio ⁇ / ⁇ ⁇ 5 is about 20%.
  • the curve 30 within region 28 illustrates the preferred circumferentially varying ratio Ar / x K s and thus the circumferentially varying offset of the radial position of the boundary wall 26 with minimum radius of curvature, with approximately half pitch between adjacent support ribs
  • Ratio ⁇ KS is about 2.5% and the offset of the radial position in the region of half pitch between two adjacent support ribs is the largest.
  • the offset of the axial position of the boundary wall 26 having the minimum radius of curvature and the offset of the radial position of the boundary wall 26 having the minimum radius of curvature and the above ratios Ax / x K s and Ar / x K s respectively change continuously and continuously preferably not linear.
  • FIG. 5 visualizes the effect of contouring the radially outer boundary wall 24 of the transition flow channel 33, FIG. 5 showing on the horizontally extending axis a ratio (pp m ) / pm between the difference (pp m ) of the static pressure p of FIG Gas flow is plotted in the transitional flow channel 14 and the mean value p m of this static pressure and the mean value p m , and wherein on the vertical axis, the dimensionless circumferential direction u / t is plotted.
  • the curve 31 of FIG. 5 corresponds to a self-adjusting according to the prior art, the course of the ratio (pp m) / p m, and the curve 32 the self-adjusting according to the invention the course of the ratio (pp m) / p m. 5, it can be seen that with the invention, an improved, uniform pressure profile of the static pressure in the circumferential direction can be provided, whereby the formation of a secondary flow in the mouth portion of thede Kunststoffströ- mung 19 in the transitional flow channel 33 can be effectively counteracted. Thereby, an unhindered entry of the cooling air flow into the transitional flow channel 3 can be ensured, whereby the efficiency of the flow machine can be improved. Furthermore, the flow in the transitional flow passage 33 between adjacent support ribs 15 can be improved.

Abstract

Intermediate housing (14), in particular of turbines (11, 13) of a gas engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24'), having a crossflow channel (33) which is formed by the bounding walls (23, 24, 24') and in which at least one supporting rib (15) is positioned which has a front edge (16), a rear edge (17) and side walls (18) which extend between the front edge (16) and the rear edge (17) and guide a gas flow which flows through the crossflow channel (33), wherein the radially outer bounding wall (24) has a contour which changes in the circumferential direction, at least in a section upstream of the supporting rib (15).

Description

ZWISCHENGEHÄUSE EINER GASTURBINE MIT EINER AUSSEN LIEGENDEN BEGRENZUNGSWAND WELCHES STROMAUFWÄRTS EINER STÜTZRIPPE EINE IN UMFANGRICHTUNG VERÄNDERNDE KONTUR AUFWEIST ZUR VERRINGERUNG DER SEKUNDÄRSTRÖMUNGSVERLUSTE  INTERMEDIATE HOUSING OF A GAS TURBINE WITH AN EXTERNAL LIMITING WALL THAT UPSTREAMS A SUPPORTING RIP A CONSTRUCTION CHANGING CONSTITUTION TO REDUCE THE SECONDARY FLOW LOSSES
Die Erfindung betrifft ein Zwischengehäuse, insbesondere von Turbinen eines Gastriebwerks, nach dem Oberbegriff des Patentanspruchs 1.  The invention relates to an intermediate housing, in particular of turbines of a gas engine, according to the preamble of patent claim 1.
Eine mehrwellige Strömungsmaschine wie zum Beispiel ein mehrwelliges Gastriebwerk verfügt über mehrere Verdichterkomponenten, mindestens eine Brennkammer und mehrere Turbinenkomponenten. So verfugt ein zwei welliges Gastriebwerk über einen Niederdruckverdichter, einen Hochdruckverdichter, mindestens eine Brennkammer, eine Hochdruck- turbine sowie eine Niederdruckturbine. Ein dreiwelliges Gastriebwerk verfugt über einen Niederdruckverdichter, einen Mitteldruckverdichter, einen Hochdruckverdichter, mindestens eine Brennkammer, eine Hochdruckturbine, eine Mitteldmckturbine und eine Niederdruckturbine. Fig. 1 zeigt einen stark schematisierten Ausschnitt aus einem mehrwelligen Gastriebwerk im Bereich eines Rotors 10 einer Hochdruckturbine 11 sowie eines Rotors 12 einer Niederdruckturbine 13. Zwischen der Hochdruckturbine 11 und der Niederdruckturbine 13 erstreckt sich ein Zwischengehäuse 14 mit einem Übergangströmungskanal 33, um die Strömung, welche die Hochdruckturbine 11 verläset, der Niederdruckturbine 13 zuzuführen, wobei im Übergangsströmungskanal 33 mindestens eine Stützrippe 15 positioniert ist. A multi-shaft turbomachine such as a multi-shaft gas engine has a plurality of compressor components, at least one combustion chamber and a plurality of turbine components. Thus, a two-shaft gas engine has a low-pressure compressor, a high-pressure compressor, at least one combustion chamber, a high-pressure turbine and a low-pressure turbine. A three-shaft gas engine has a low-pressure compressor, a medium-pressure compressor, a high-pressure compressor, at least one combustion chamber, a high-pressure turbine, a Mitteldmckturbine and a low-pressure turbine. 1 shows a highly schematic section of a multi-shaft gas engine in the region of a rotor 10 of a high-pressure turbine 11 and a rotor 12 of a low-pressure turbine 13. Between the high-pressure turbine 11 and the low-pressure turbine 13, an intermediate housing 14 with a transition flow channel 33 extends to the flow, which leaves the high pressure turbine 11 to supply the low pressure turbine 13, wherein in the transitional flow channel 33 at least one support rib 15 is positioned.
Bei der Stützrippe 15 handelt es sich um ein statorseitiges Bauteil, welches die den Übergangsströmungskanal 33 durchströmende Strömung führt. Eine solche Strömungsfuhrende Stützrippe 15 verfügt über eine Vorderkante 16, die auch als Strömungseintrittskante be- zeichnet wird, über eine Hinterkante 17, die auch als Strömungsaustrittskante bezeichnet wird, und über Seitenwände 18. The support rib 15 is a stator-side component, which carries the flow flowing through the transition flow channel 33. Such a flow-guiding support rib 15 has a front edge 16, which is also referred to as a flow inlet edge, via a rear edge 17, which is also referred to as a flow outlet edge, and via side walls 18.
In den Übergangströmungskanal 33 kann (siehe Fig. 1) stromaufwärts der Stützrippen 15 im Bereich eines Eintritts in den Übergangsströmungskanal 33 bzw. im Bereich einer Vor- derkante 34 des Zwischengehäuses 14 radial außen in denselben eine Kavität 19 münden, durch die in geringem Maße Kühlluft 21a austreten kann, die sich mit der die Hochdruck-In the transition flow channel 33 can (see Fig. 1) upstream of the support ribs 15 in the region of an entry into the transitional flow channel 33 or in the region of a leading edge 34 of the intermediate housing 14 radially outwardly in the same open a cavity 19, through which a small amount of cooling air 21a, which deals with the high pressure
BESTÄTIGUNGSKOPIE turbine 11 verlassenden Gasströmung 20 vermischt. Diese Kavität 19 befindet sich zwischen den NDT-Gehäuse und dem Zwischengehäuse 14, die mit einer Dichtung 21 c abgedichtet wird. Durch diese Dichtung 21c fließt nur eine schwache Leckage Strömung 21b, da das NDT-Gehäuse und das Zwischengehäuse 14 nicht fest miteinander verbunden werden können. CONFIRMATION COPY turbine 11 leaving gas flow 20 mixed. This cavity 19 is located between the NDT housing and the intermediate housing 14, which is sealed with a seal 21 c. Only a weak leakage flow 21b flows through this seal 21c, since the NDT housing and the intermediate housing 14 can not be firmly connected to each other.
Um den Eintritt der Leckage 21a in den Übergangsströmungskanal 33 zu ermöglichen und ein Einströmen der Gasströmung 20 über die Kavität 19 zu verhindern, liegt der statische Druck der Gasströmung 20 im Bereich des Eintritts in die Kavität 19 unterhalb des Drucks der Kühlluft 21b im Sekundärluftbereich 21d außerhalb des Ringraumes. In order to allow the leakage 21a to enter into the transitional flow passage 33 and to prevent the gas flow 20 from flowing in through the cavity 19, the static pressure of the gas flow 20 in the area of entry into the cavity 19 is below the pressure of the cooling air 21b in the secondary air area 21d of the annulus.
Wie Fig. 2 entnommen werden kann, stellt sich bei der aus dem Stand der Technik gemäß Fig. 1 bekannten Strömungsmaschine stromaufwärts der Vorderkanten 16 der Stützrippen 15 in Folge einer Verblockung der den Übergangsströmungskanal 33 durchströmenden Gasströmung auf Umfangspositionen, auf welchen die Stützrippen positioniert sind, ein Druckanstieg +Δρ des statischen Drucks ein, wohingegen sich gemäß Fig. 2 auf Umfangspositionen zwischen benachbarten Stützrippen 15 ein Druckabfall -Δρ des statischen Drucks einstellt. In Fig. 2 ist eine dimensionslose Umfangsrichtung u/t gezeigt, wobei t der Stützrippenteilung in Umfangsrichtung u entspricht. As can be seen from FIG. 2, in the turbomachine known from the prior art according to FIG. 1, upstream of the front edges 16 of the support ribs 15, as a result of blocking of the gas flow flowing through the transition flow duct 33, to circumferential positions on which the support ribs are positioned. a pressure increase + Δρ of the static pressure, whereas according to FIG. 2 at circumferential positions between adjacent support ribs 15, a pressure drop -Δρ of the static pressure adjusts. FIG. 2 shows a dimensionless circumferential direction u / t, where t corresponds to the support rib pitch in the circumferential direction u.
Die in Fig. 2 durch gestrichelte Linien dargestellten Druckfelder des Druckanstiegs +Δρ auf der Umfangsposition der Stützrippen 1 und des Druckabfalls -Δρ auf der Umfangspo- sition zwischen benachbarten Stützrippen 15 jeweils stromaufwärts der Vorderkanten 16 der Stützrippen 15 reicht in die Kavität 19 hinein, sodass sich im Mündungsbereich der Kavität 19 und im Übergangsströmungskanal 33 eine verlustbehaftete Sekundärströmung 22 ausbildet, Weiter führt die Druckschwankung gemäß Fig. 2 in der Kavität zu einem höheren Druckgefälle zwischen der Gasströmung 20 und der Kühllüftströmung 21b, was letztendlich die Leckage erhöht und zu einem verschlechterten Wirkungsgrad der Strömungsmaschine führt. Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein Zwischengehäuse zu schaffen, mit Hilfe dessen der Wirkungsgrad gesteigert werden kann. The pressure fields of the pressure increase Δρ on the circumferential position of the support ribs 1 and the pressure drop Δρ at the circumferential position between adjacent support ribs 15 respectively upstream of the leading edges 16 of the support ribs 15 are shown in dashed lines in the cavity 19 so that Further, the pressure fluctuation of FIG. 2 in the cavity leads to a higher pressure gradient between the gas flow 20 and the cooling air flow 21b, which ultimately increases the leakage and degraded efficiency the turbomachine leads. On this basis, the present invention is based on the problem to provide an intermediate housing, by means of which the efficiency can be increased.
Dieses Problem wird durch ein Zwischengehäuse gemäß Anspruch 1 gelöst. This problem is solved by an intermediate housing according to claim 1.
Erfindungsgemäß weist die radial außen liegende Begrenzungswand zumindest in einem Abschnitt stromaufwärts der Stützrippe eine sich in Umfangsrichtung verändernde Kontur auf. According to the invention, the radially outer boundary wall has a contour which changes in the circumferential direction at least in a section upstream of the support rib.
Mit der Erfindung ist es möglich, der Ausbildung der sich nach dem Stand der Technik im Kühlluftströmungskanal einstellenden, verlustbehafteten Sekundärströmung effizient entgegen zu wirken. Da mit einem geringeren Druckgefälle zwischen der Gasströmung und der Kühlluftströmung gearbeitet werden kann, kann der Wirkungsgrad gegenüber dem Stand der Technik verbessert werden. With the invention, it is possible to effectively counteract the formation of the state of the art in the cooling air flow channel adjusting, lossy secondary flow. Since it is possible to work with a lower pressure gradient between the gas flow and the cooling air flow, the efficiency can be improved compared to the prior art.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt: Fig. 1 einen stark schematisierten, ausschnitts weisen Längsschnitt durch eine aus dem Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. 1 shows a highly schematic, partial longitudinal section through one of the
Stand der Technik bekannte Strömungsmaschine im Bereich eines Zwischengehäuses und damit Strömungskanals zwischen zwei Turbinenkomponenten; Fig. 2 einen Ausschnitt aus der Anordnung der Fig. 1 in radialer Blickrichtung;  Prior art known turbomachine in the region of an intermediate housing and thus flow channel between two turbine components; 2 shows a detail of the arrangement of Figure 1 in the radial direction.
Fig. 3 einen stark schematisierten, ausschnittsweisen Längsschnitt durch eine Strö- mungsmaschine im Bereich eines erfindungsgemäßen Zwischengehäuses, das zwischen zwei Turbinenkomponenten positioniert ist; 3 is a highly schematic, fragmentary longitudinal section through a flow machine in the region of an intermediate housing according to the invention, which is positioned between two turbine components;
Fig. 4 ein Diagramm zur Verdeutlichung der Erfindung; und Fig. 4 is a diagram for illustrating the invention; and
Fig. 5 ein weiteres Diagramm zur Verdeutlichung der Erfindung. Fig. 5 is another diagram for illustrating the invention.
Die hier vorliegende Erfindung betrifft den Bereich mehrwelliger Strömungsmaschinen, insbesondere mehrwelliger Gastriebwerke, mit mehreren Verdichterkomponenten sowie mehreren Turbinenkomponenten. Der grundsätzliche Aufbau einer solchen Strömungsmaschine ist dem hier angesprochenen Fachmann geläufig und wurde bereits im Zusammenhang mit Fig. 1 beschrieben. Die hier vorliegende Erfindung betrifft nun Details eines Zwischengehäuses 14 einer derartigen Strömungsmaschine, mithilfe derer der Eintritt einer in einem ühlluftströmungska- nal 19 geführten Kühlluftströmung in die vom Übergangsströmungskanal 33 des Zwischengehäuses 14 geführte Gasströmung verbessert werden kann, nämlich in einem Eintrittsbereich des Übergangsströmungskanals 33 stromaufwärts von im Übergangsströ- mungskanal 33 positionierten Stützrippen 15. The present invention relates to the field of multi-shaft turbomachinery, in particular multi-shaft gas engines, with several compressor components and several turbine components. The basic structure of such a turbomachine is familiar to the person skilled in the art and has already been described in connection with FIG. The present invention now relates to details of an intermediate housing 14 of such a turbomachine, by means of which the entry of a guided in a ühlluftströmungska- channel 19 cooling air flow can be improved in the guided by the transitional flow channel 33 of the intermediate housing 14 gas flow, namely in an inlet region of the transitional flow channel 33 upstream of in the transitional flow channel 33 positioned support ribs 15th
Die Erfindung ist sowohl bei einem Zwischengehäuse 14 einer zweiwelligen Strömungsmaschine, das sich zwischen einer Hochdruckturbine 11 sowie eine Niederdruckturbine 13 erstreckt, als auch bei einem Zwischengehäuse einer dreiwelligen Strömungsmaschine, das sich zwischen einer Hochdruckturbine und einer Mitteldruckturbine oder zwischen einer Mitteldruckturbine und einer Niederdruckturbine erstreckt, einsetzbar. The invention is applicable both to an intermediate housing 14 of a twin-shaft turbomachine which extends between a high-pressure turbine 11 and a low-pressure turbine 13, and to an intermediate housing of a three-shaft turbomachine which extends between a high-pressure turbine and a medium-pressure turbine or between a medium-pressure turbine and a low-pressure turbine, used.
Fig. 3 zeigt einen Ausschnitt aus einer Strömungsmaschine im Bereich eines Zwischengehäuses 14, eines Übergangsströmungskanals 33 dieses Zwischengehäuses 14 und einer stromaufwärts des Übergangsströmungskanals 33 positionierten, im gezeigten Ausführungsbeispiel als Hochdruckturbine 11 ausgebildeten Turbinenkomponente, wobei gemäß Fig. 3 der Kühlluftströmungskanal 19 von radial außen in den Übergangsströmungskanal 33 mündet, nämlich stromaufwärts von Stützrippen 15, die im Übergangsströmungskanal 33 positioniert sind. Der Kühlluftströmungskanal 19 wird dabei von der Vorderkante 34 des Zwischengehäuses 14 abschnittsweise begrenzt. 3 shows a section of a turbomachine in the region of an intermediate housing 14, a transitional flow channel 33 of this intermediate housing 14 and a turbine component positioned upstream of the transitional flow channel 33, designed as a high-pressure turbine 11 in the exemplary embodiment shown. FIG. 3 shows the cooling air flow channel 19 from the radially outward direction the transitional flow channel 33 opens, namely upstream of support ribs 15 which are positioned in the transitional flow channel 33. The cooling air flow channel 19 is thereby limited in sections by the front edge 34 of the intermediate housing 14.
Der Übergangsströmungskanal 33 wird radial innen von einer statorseitigen Begrenzungswand 23 und radial außen ebenfalls von einer statorseitigen Begrenzungswand 24 begrenzt. An den Rotor 10 der Hochdruckturbine 11 grenzt radial außen eine Begrenzungswand 25 der Hochdruckturbine 11 an. Um nun einen ungehinderten Eintritt der vom Kühlluftströmungskanal 19 geführten Kühlluft in die die Hochdruckturbine 11 verlassende und vom Übergangsströmungskanal 33 des Zwischengehäuses 14 geführte Gasströmung zu ermöglichen, kann die radial außen liegen- de Begrenzungs wand 24 des Übergangsströmungskanals 33 zumindest in einem Abschnitt stromaufwärts der Stützrippen 15 mit einer sich in Umfangsrichtung verändernden Kontur versehen sein. The transitional flow channel 33 is bounded radially inwardly by a stator-side boundary wall 23 and also radially on the outside by a stator-side boundary wall 24. A boundary wall 25 of the high-pressure turbine 11 adjoins the rotor 10 of the high-pressure turbine 11 radially on the outside. In order now to permit unimpeded entry of the cooling air guided from the cooling air flow channel 19 into the gas flow leaving the high-pressure turbine 11 and guided by the transition flow channel 33 of the intermediate housing 14, the radially outer boundary wall 24 of the transition flow channel 33 can be located at least in a section upstream of the support ribs 15 be provided with a circumferentially changing contour.
Vorzugsweise weist die radial außen liegende Begrenzungswand 24 des Übergangsströ- mungskanals 33 zumindest in einem Übergangsabschnitt zwischen der Vorderkante 34 des Zwischengehäuses 14 und dem Übergangsströmungskanals 33 eine sich in Umfangsrichtung verändernde Kontur auf. Preferably, the radially outer boundary wall 24 of the transitional flow channel 33 at least in a transition section between the front edge 34 of the intermediate housing 14 and the transitional flow channel 33 has a circumferentially changing contour.
Diese sich in Umfangsrichtung verändernde Kontur der radial außen liegenden Begren- zungswand 24 des Übergangsströmungskanals 33 kann sich gemäß Fig. 3 auch bis in einen Bereich stromabwärts der Vorderkanten 16 der Stützrippen 15 erstrecken, wobei Fig. 3 zwei an unterschiedlichen Umfangpositionen u/t ausgebildete Konturen 24 und 24' für die radial äußere Begrenzungs wand des Übergangsströmungskanals 33 zeigt. Die radial außen liegende Begrenzungswand 24 des Übergangsströmungskanals 33 verfugt im Eintrittsbereich des Übergangsströmungskanals 33 stromaufwärts der Vorderkanten 16 der Stützrippen 15 über einen Begrenzungs wandabschnitt bzw. Begrenzungswandpunkt 26 mit minimalem Krümmungsradius und demnach maximaler Krümmung. Die Kontur der radial außen liegenden Begrenzungswand 24 des Übergangsströmungskanals 33 verändert sich dabei in Umfangsrichtung, u bzw. u/t derart, dass sich eine Axialposition (Axialrichtung x) und/oder einer Radialposition (Radialrichtung r) des Begrenzungswandabschnitts bzw. Begrenzungswandpunkts 26 mit minimalem Krümmungsradius in Umfangsrichtung u bzw. u t verändert. Vorzugsweise verändert sich in Umfangsrichtung sowohl die Axialposition als auch die Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius. In einer vereinfachten Ausfuhrung der Erfindung ist es jedoch auch möglich, dass sich ausschließlich die Axialposition oder ausschließlich die Radialposition dieses Begrenzungswand- punkts 26 in Umfangsrichtung verändert. According to FIG. 3, this circumferentially changing contour of the radially outer boundary wall 24 of the transition flow channel 33 can also extend into a region downstream of the leading edges 16 of the support ribs 15, FIG. 3 showing two contours formed at different circumferential positions u / t 24 and 24 'for the radially outer boundary wall of the transitional flow channel 33 shows. The radially outer boundary wall 24 of the transition flow channel 33 has in the inlet region of the transition flow channel 33 upstream of the leading edges 16 of the support ribs 15 via a boundary wall section or boundary wall 26 with a minimum radius of curvature and thus maximum curvature. The contour of the radially outer boundary wall 24 of the transition flow channel 33 changes in the circumferential direction, u or u / t such that an axial position (axial direction x) and / or a radial position (radial direction r) of the boundary wall section or boundary wall point 26 with minimal Radius of curvature in the circumferential direction u or ut changed. Preferably, in the circumferential direction, both the axial position and the radial position of the boundary wall point 26 change with a minimum radius of curvature. In a simplified embodiment of the invention, however, it is also possible that only the axial position or exclusively the radial position of this Begrenzungswand- point 26 changes in the circumferential direction.
Die Axialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius verändert sich in Umfangsrichtung u bzw. u/t derart, dass in etwa auf der Umfangsposition der Vorderkanten 16 der Stützrippen 15 dieser Begrenzungswandpunkt 26 in Axialrichtung x maximal stromaufwärts und in etwa auf einer Umfangsposition halber Teilung zwischen zwei benachbarten Stützrippen in Axialrichtung x maximal stromabwärts versetzt bzw. positioniert ist. Zwischen diesen maximalen stromaufwärtigen und stromab wältigen Axialpositionen verändert sich die Axialposition des Begrenzungswandpunkts 26 in Umfangsrichtung kontinuierlich bzw. stetig. The axial position of the boundary wall 26 with minimal radius of curvature changes in the circumferential direction u or u / t such that approximately at the circumferential position of the leading edges 16 of the support ribs 15 this boundary wall 26 in the axial direction x maximum upstream and approximately in a circumferential position half pitch between two adjacent supporting ribs in the axial direction x offset or positioned downstream of maximum. Between these maximum upstream and downstream from axial positions, the axial position of the boundary wall point 26 changes continuously or continuously in the circumferential direction.
Die Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius verändert sich in Umfangsrichtung u bzw. u/t derart, dass in etwa auf der Umfangsposition der Vorderkanten 16 der Stützrippen 15 dieser Begrenzungswandpunkt 26 in Radialrichtung r maximal nach radial außen und in etwa auf einer Umfangsposition halber Teilung zwischen zwei benachbarten Stützrippen 15 in Radialrichtung r maximal nach radial innen versetzt bzw. positioniert ist. Zwischen diesen maximalen radial inneren und radial äußeren Radialpositionen verändert sich die Radialposition des Begrenzungswandpunkts 26 in Umfangsrichtung kontinuierlich bzw. stetig. Die in Fig. 3 gezeigte Kontur 24 der radial äußeren Begrenzungswand des Übergangsströmungskanals 33 entspricht der Kontur derselben in etwa auf der Umfangsposition einer Vorderkante 16 einer Stützrippe 1 , wohingegen die in Fig. 3 gezeigte Kontur 24' der Kontur derselben in etwa auf einer Umfangsposition halber Teilung zwischen zwei benachbarten Stützrippen 15 entspricht. Weitere Details hinsichtlich des Versatzes der Axialposition sowie Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius in Umfangsrichtung u bzw. u/t werden nachfolgend unter Bezugnahme auf Fig. 4 beschrieben. In Fig. 4 ist auf der horizontal verlaufenden Achse ein betragsmäßiges Verhältnis ΔΧ/XKS zwischen dem Axialabstand Δχ (siehe Fig. 3) der stromabwärtigen Axialposition und der maximal stromaufwärtigen Axialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius und dem Axialabstand KS (siehe Fig. 3) eines stromabwärtigen Endes 27 der radial außenliegenden Begrenzungswand 25 der stromaufwärts des Übergangskanals 33 positionierten Turbinenkomponente 11 und der Vorderkante 16 der Stützrippen 15 aufgetragen. Weiterhin ist in Fig. 4 auf der horizontal verlaufenden Achse ein betragsmäßiges Verhältnis ΔΓ/XKS zwischen dem Radialabstand Ar (siehe Fig. 3) der maximal radial äußeren Radialposition und der radial inneren Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius und diesem Axialabstand xKs aufgetragen. Wie bereits erwähnt, entspricht S (siehe Fig. 3) dem Abstand zwischen dem stromabwärtigen Ende 27 der radial außenliegenden Begrenzungswand 25 der Hochdruckturbine 11 und der Vorderkante 16 der Stützrippen 15. The radial position of the boundary wall 26 with minimal radius of curvature changes in the circumferential direction u or u / t such that approximately at the circumferential position of the leading edges 16 of the support ribs 15 of this boundary wall 26 in the radial direction r maximum radially outward and approximately in a circumferential position half pitch between two adjacent support ribs 15 in the radial direction r is offset or positioned maximally radially inward. Between these maximum radially inner and radially outer radial positions, the radial position of the boundary wall point 26 changes continuously or continuously in the circumferential direction. The contour 24 shown in Fig. 3 of the radially outer boundary wall of the transition flow channel 33 corresponds to the contour thereof approximately at the circumferential position of a front edge 16 of a support rib 1, whereas the contour shown in Fig. 3 24 'of the same contour approximately in a circumferential position Division between two adjacent support ribs 15 corresponds. Further details regarding the offset of the axial position and the radial position of the boundary wall point 26 with a minimum radius of curvature in the circumferential direction u or u / t are described below with reference to FIG. 4. In Fig. 4 is on the horizontal axis an absolute value ΔΧ / X K S between the axial distance Δχ (see Fig. 3) of the downstream axial position and the maximum upstream axial position of the boundary wall 26 with minimum radius of curvature and the axial distance KS (see FIG. 3) of a downstream end 27 of the radially outer boundary wall 25 of the upstream of the transition channel 33 positioned turbine component 11 and the leading edge 16 of the support ribs 15 applied. Furthermore, an absolute value ΔΓ / XKS between the radial distance Ar (see FIG. 3) of the maximum radially outer radial position and the radially inner radial position of the boundary wall point 26 with a minimum radius of curvature and this axial distance x K s is plotted on the horizontally extending axis in FIG , As already mentioned, S (see FIG. 3) corresponds to the distance between the downstream end 27 of the radially outer boundary wall 25 of the high-pressure turbine 11 and the front edge 16 of the support ribs 15.
Auf der vertikal verlaufenden Achse ist in Fig. 4 die dimensionslose Umfangsrichtung u t aufgetragen, wobei auf den Umfangspositionen u/t=0 und u/t=l jeweils eine Vorderkante 16 einer Stützrippe 15 positioniert ist, und wobei eine Umfangsposition u/t-0.5 einer Um- fangsposition in der Mitte zwischen zwei benachbarten Stützrippen 15 entspricht. On the vertical axis in Fig. 4, the dimensionless circumferential direction ut is plotted, wherein on the circumferential positions u / t = 0 and u / t = l are each a leading edge 16 of a support rib 15 is positioned, and wherein a circumferential position u / t-0.5 corresponds to a circumferential position in the middle between two adjacent support ribs 15.
So kann Fig. 4 entnommen werden, dass sich die Verhältnisse ΔΧ/X S und ΔΓ/X S in dimen- sionsloser Umfangsrichtung u/t gesehen zwischen zwei benachbarten Stützrippen 15 kontinuierlich verändern, wobei auf der Umfangsposition u/t=0.5 von in etwa halber Teilung zwischen zwei benachbarten Stützrippen 15 das Verhältnis ΔΧ/XKS und damit der Versatz der Axialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius nach stromabwärts sowie das Verhältnis ΔΓ/XKS und damit der Versatz der Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius nach radial innen am größten sind, und in etwa auf den Umfangspositionen u/t=0 und u/t=l, auf denen die Vorder- kanten 16 der Stützrippen 15 positioniert sind, diese Verhältnisse und damit Versätze am Kleinsten sind. Thus, it can be seen from FIG. 4 that the ratios .DELTA.Χ / XS and .DELTA.Γ / XS vary continuously between two adjoining support ribs 15 in the circumferential direction u / t, wherein on the circumferential position u / t = 0.5 of approximately half the pitch between two adjacent support ribs 15, the ratio ΔΧ / XKS and thus the offset of the axial position of the boundary wall 26 with minimum radius of curvature downstream and the ratio ΔΓ / X K S and thus the offset of the radial position of the boundary wall 26 with the minimum radius of curvature radially inward are greatest , and approximately on the circumferential positions u / t = 0 and u / t = l, on which the front edges 16 of the support ribs 15 are positioned, these ratios and thus offsets are the smallest.
Der Bereich 28 der Fig. 4 visualisiert einen bevorzugten Gültigkeitsbereich für das sich in Umfangsrichtung u bzw. u t verändernde Verhältnis ΔΧ/XKS und/oder Ar/x^s und damit den sich in Umfangsrichtung u bzw. u/t verändernden Versatz der Axialposition und/oder der Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius. The region 28 of FIG. 4 visualizes a preferred range of validity for the ratio ΔΧ / XKS and / or Ar / x ^ s changing in the circumferential direction u or ut and thus the offset of the axial position u and u / t changing in the circumferential direction u or u / t / or the radial position of the boundary wall 26 with a minimum radius of curvature.
Die Verhältnisse Ax/xKs und ΔΓ/X S betragen bis zu 40%. The ratios Ax / x K s and ΔΓ / XS are up to 40%.
Die Verhältnisse A /xKs und Ar/xus betragen auf der Umfangsposition u/t=0.5 von in etwa halber Teilung zwischen zwei Stützrippen 15 maximal 40% und minimal 2%. Die Verhältnisse ΔΧ/X S und ΔΓ/X S betragen auf den Umfangspositionen u/t=0 und u/t=l 0%. Dazwischen verändern sich diese Verhältnisse ΔΧ/XKS und Ar/xKs kontinuierlich, steig und vor- zugsweise nicht linear. The ratios A / x K s and Ar / xus are at the circumferential position u / t = 0.5 of about half pitch between two support ribs 15 maximum 40% and a minimum of 2%. The ratios ΔΧ / XS and ΔΓ / XS are on the circumferential positions u / t = 0 and u / t = l 0%. In between, these ratios ΔΧ / X K s and Ar / x K s change continuously, rising and preferably not linearly.
Insbesondere beträgt das sich in Umfangsrichtung u bzw. u/t verändernde Verhältnis In particular, the ratio changes in the circumferential direction u or u / t
ΔΧ/X S auf der Umfangsposition u/t=0.5 von in etwa halber Teilung zwischen zwei Stützrippen 15 insbesondere zwischen 2% und 25%. ΔΧ / X S at the circumferential position u / t = 0.5 of approximately half the pitch between two support ribs 15, in particular between 2% and 25%.
Das sich in Umfangsrichtung u bzw. u/t verändernde Verhältnis Ar/xKs beträgt auf der Umfangsposition u/t=0.5 von in etwa halber Teilung zwischen zwei Stützrippen 15 insbesondere zwischen 2% und 5%. Die Kurve 29 innerhalb des Bereichs 28 visualisiert das bevorzugte, sich in Umfangsrichtung verändernde Verhältnis AX/X S und damit den sich in Umfangsrichtung verändernden Versatz der Axialposition des Begrenzungswandpunkts 26 mit minimalem Kriirnmungsra- dius, wobei gemäß der Kurve 29 der Versatz der Axialposition im Bereich halber Teilung zwischen zwei benachbarten Stützrippen am Größten ist und das Verhältnis Δχ/χΚ5 in etwa 20% beträgt. Die Kurve 30 innerhalb des Bereichs 28 verdeutlicht das bevorzugte, sich in Umfangsrich- tung verändernde Verhältnis Ar/xKs und damit den sich in Umfangsrichtung verändernden Versatz der Radialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius, wobei bei in etwa halber Teilung zwischen benachbarten Stützrippen das Verhältnis ΔΓ KS in etwa 2.5% beträgt und der Versatz der Radialposition im Bereich halber Teilung zwischen zwei benachbarten Stützrippen am Größten ist. The ratio Ar / x K s changing in the circumferential direction u or u / t is on the circumferential position u / t = 0.5 of approximately half the pitch between two support ribs 15, in particular between 2% and 5%. The curve 29 within the range 28 visualizes the preferred circumferentially varying ratio AX / XS and thus the circumferentially varying offset of the axial position of the minimum crimp radius limiting wall point 26, where the offset of the axial position is in the range of half Division between two adjacent support ribs is the largest and the ratio Δχ / χ Κ5 is about 20%. The curve 30 within region 28 illustrates the preferred circumferentially varying ratio Ar / x K s and thus the circumferentially varying offset of the radial position of the boundary wall 26 with minimum radius of curvature, with approximately half pitch between adjacent support ribs Ratio ΔΓ KS is about 2.5% and the offset of the radial position in the region of half pitch between two adjacent support ribs is the largest.
In Umfangsrichtung gesehen verändern sich der Versatz der Axialposition des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius und der Versatz der Radialpositi- on des Begrenzungswandpunkts 26 mit minimalem Krümmungsradius bzw. die obigen Verhältnisse Ax/xKs und Är/xKs jeweils kontinuierlich bzw. stetig und vorzugsweise nicht linear. In the circumferential direction, the offset of the axial position of the boundary wall 26 having the minimum radius of curvature and the offset of the radial position of the boundary wall 26 having the minimum radius of curvature and the above ratios Ax / x K s and Ar / x K s respectively change continuously and continuously preferably not linear.
Fig. 5 visualisiert den Effekt der erfmdungsgemäßen Konturierung der radial außen liegen- den Begrenzungswand 24 des Übergangsströmungskanals 33 wobei in Fig. 5 auf der horizontal verlaufenden Achse ein Verhältnis (p-pm)/pm zwischen der Differenz (p-pm) des statischen Drucks p der Gasströmung im Übergangsströmungskanal 14 und dem Mittelwert pm dieses statischen Drucks und dem Mittelwert pm aufgetragen ist, und wobei auf der vertikal verlaufenden Achse die dimensionslose Umfangsrichtung u/t aufgetragen ist. FIG. 5 visualizes the effect of contouring the radially outer boundary wall 24 of the transition flow channel 33, FIG. 5 showing on the horizontally extending axis a ratio (pp m ) / pm between the difference (pp m ) of the static pressure p of FIG Gas flow is plotted in the transitional flow channel 14 and the mean value p m of this static pressure and the mean value p m , and wherein on the vertical axis, the dimensionless circumferential direction u / t is plotted.
Die Kurve 31 der Fig. 5 entspricht einem sich nach dem Stand der Technik einstellenden Verlauf des Verhältnisses (p-pm)/pm und die Kurve 32 dem sich nach der Erfindung einstellenden Verlauf des Verhältnisses (p-pm)/pm. Fig. 5 kann entnommen werden, dass mit der Erfindung ein verbesserter, gleichförmiger Druckverlauf des statischen Drucks in Umfangsrichtung bereitgestellt werden kann, wodurch der Ausbildung einer Sekundärströmung im Mündungsabschnitt des Kühlluftströ- mungskanals 19 in den Übergangsströmungskanal 33 effektiv entgegengewirkt werden kann. Dadurch kann ein ungehinderter Eintritt der Kühlluftströmung in den Übergangs- Strömungskanal 3 gewährleistet werden, wodurch der Wirkungsgrad der Strömungsma- schine verbessert werden kann. Weiterhin kann die Strömung im Übergangsströmungskanal 33 zwischen benachbarten Stützrippen 15 verbessert werden. The curve 31 of FIG. 5 corresponds to a self-adjusting according to the prior art, the course of the ratio (pp m) / p m, and the curve 32 the self-adjusting according to the invention the course of the ratio (pp m) / p m. 5, it can be seen that with the invention, an improved, uniform pressure profile of the static pressure in the circumferential direction can be provided, whereby the formation of a secondary flow in the mouth portion of the Kühlluftströ- mung 19 in the transitional flow channel 33 can be effectively counteracted. Thereby, an unhindered entry of the cooling air flow into the transitional flow channel 3 can be ensured, whereby the efficiency of the flow machine can be improved. Furthermore, the flow in the transitional flow passage 33 between adjacent support ribs 15 can be improved.

Claims

Patentansprüche claims
1. Zwischengehäuse (.14), insbesondere von Turbinen (11, 13) eines Gastriebwerks, mit einer radial innen liegenden Begrenzungswand (23) und mit einer radial außen liegenden Begrenzungswand (24, 24'), mit einem Übergangsströmungskanal (33), der durch die Begrenzungswände (23, 24, 24') gebildet ist und in dem mindestens eine Stützrippe (15) positioniert ist, die eine Vorderkante (16), eine Hinterkante (17) sowie sich zwischen der Vorderkante (16) und der Hinterkante (17) erstreckende, eine den Übergangsströmungskanal (33) durchströmende Gasströmung f hrende Seitenwände (18) aufweist, dadurch gekennzeichnet, dass die radial außen liegende Begrenzungswand (24) zumindest in einem Abschnitt stromaufwärts der Stützrippe (15) eine sich in Umfangsrichtung verändernde Kontur aufweist. 1. intermediate housing (.14), in particular of turbines (11, 13) of a gas engine, with a radially inner boundary wall (23) and with a radially outer boundary wall (24, 24 '), with a transitional flow channel (33) is formed by the boundary walls (23, 24, 24 ') and in which at least one support rib (15) is positioned having a leading edge (16), a trailing edge (17) and between the leading edge (16) and the trailing edge (17 ), one of the transition flow channel (33) flowing through gas flow fHorden side walls (18), characterized in that the radially outer boundary wall (24) at least in a portion upstream of the support rib (15) has a circumferentially changing contour.
2. Zwischengehäuse (14) nach Anspruch 1, dadurch gekennzeichnet, dass die radial außen liegende Begrenzungswand (24) des Übergangsströmungskanals (33) zumindest in einem Übergangsabschnitt zwischen einer Vorderkante (34) des Zwischengehäuses (14) und dem Übergangsströmungskanals (33) eine sich in Umfangsrichtung verändernde Kontur aufweist. Second intermediate housing (14) according to claim 1, characterized in that the radially outer boundary wall (24) of the transition flow channel (33) at least in a transition section between a front edge (34) of the intermediate housing (14) and the transition flow channel (33) a Having circumferentially changing contour.
3. Zwischengehäuse (14) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass sich die Kontur der radial außen liegenden Begrenzungswand (24) derart verändert, dass sich eine Axialposition eines Begrenzungswandabschnitts bzw. eines Begrenzungswandpunkts (26) mit minimalem Kmrnmungsradius in Umfangsrichtung verändert. 3. intermediate housing (14) according to claim 1 or 2, characterized in that the contour of the radially outer boundary wall (24) changed such that an axial position of a boundary wall portion or a Begrenzungswandpunkts (26) changes with minimal Kmrnmungsradius in the circumferential direction.
4. Zwischengehäuse (14) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass sich die Kontur der radial außen liegenden Begrenzungswand (24) derart verändert, dass sich eine Radialposition eines Begrenzungswandabschnitts bzw. eines Begrenzungswandpunkts (26) mit minimalem Krümmungsradius in Umfangsrichtung verändert. 4. intermediate housing (14) according to claim 1 or 2, characterized in that the contour of the radially outer boundary wall (24) changed such that changes a radial position of a boundary wall portion or a boundary wall point (26) with a minimum radius of curvature in the circumferential direction.
5. Zwischengehäuse (14) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass sich die Kontur der radial außen liegenden Begrenzungswand (24) derart verändert, dass sich eine Axialposition und eine Radialposition eines Begrenzungswandabschnitts bzw. eines Begrenzungswandpunkts (26) mit minimalem Krümmungsradius in Umfangsrichtung verändert. 5. intermediate housing (14) according to claim 1 or 2, characterized in that the contour of the radially outer boundary wall (24) changed such that a Altered axial position and a radial position of a boundary wall portion or a boundary wall point (26) with a minimum radius of curvature in the circumferential direction.
Zwischengehäuse (14) nach Anspruch 3 oder 5, dadurch gekennzeichnet, dass sich die Axialposition des Begrenzungswandabschnitts bzw. Begrenzungswandpunkts (26) mit minimalem -rümmungsradius in Umfangsrichtung derart verändert, dass in etwa auf der Um- fangsposition von Vorderkanten (16) der Stützrippen (15) dieser Begrenzungswandpunkt (26) maximal stromaufwärts und in etwa auf einer Umfangsposition halber Teilung zwischen zwei benachbarten Stützrippen maximal stromabwärts positioniert ist. Intermediate housing (14) according to claim 3 or 5, characterized in that the axial position of the Begrenzungswandabschnitts or Begrenzungswandpunkts (26) with minimal radius of curvature in the circumferential direction changed such that approximately at the circumferential position of leading edges (16) of the support ribs ( 15) of this boundary wall point (26) is positioned maximally upstream and approximately at a circumferential position half pitch between two adjacent support ribs maximally downstream.
Zwischengehäuse (14) nach Anspruch 6, dadurch gekennzeichnet, dass ein betragsmäßiges Verhältnis zwischen dem Axialabstand der strömabwärtigen und der maximal stromauf- wärtigen Axialposition des Begrenzungswandpunkts (26) mit minimalem Krümmungsradius und dem Axialabstand eines strömabwärtigen Endes (27) einer radial außen liegenden Begrenzungswand (25) einer stromaufwärts des Übergangsströmungskanals (33) positionierten Turbinenkomponente (11) und der Vorderkante (16) der Stützrippen (15) bis zu 40% beträgt. Intermediate housing (14) according to claim 6, characterized in that an absolute value between the axial distance of the strömabwärtigen and the maximum upstream axial position of the Begrenzungswandpunkts (26) with a minimum radius of curvature and the axial distance of a strömabwärtigen end (27) of a radially outer boundary wall ( 25) of a turbine component (11) positioned upstream of the transitional flow passage (33) and the leading edge (16) of the support ribs (15) is up to 40%.
Zwischengehäuse (14) nach Anspruch 7, dadurch gekennzeichnet, dass das Verhältnis bis zu 25% beträgt. Intermediate housing (14) according to claim 7, characterized in that the ratio is up to 25%.
Zwischengehäuse (14) nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass sich die Radialposition des Begrerizungswandabschnitts bzw. Begrenzungswandpunkts (26) mit minimalem Krümmungsradius in Umfangsrichtung derart verändert, dass in etwa auf der Umfangsposition von Vorderkanten (16) der Stützrippen (15) dieser Begrenzungswandpunkt (26) maximal radial außen und in etwa auf einer Umfangsposition halber Teilung zwischen zwei benachbarten Stützrippen maximal radial innen positioniert ist. Intermediate housing (14) according to claim 4 or 5, characterized in that the radial position of the Begrungungsungswandabschnitts or Begrenzungswandpunkts (26) with a minimum radius of curvature in the circumferential direction changed such that approximately at the circumferential position of leading edges (16) of the support ribs (15) of this Boundary wall point (26) is maximally positioned radially outward and approximately at a circumferential position half pitch between two adjacent support ribs maximally radially inward.
Zwischengehäuse (14) nach Anspruch 8, dadurch gekennzeichnet, dass ein betragsmäßiges Verhältnis zwischen dem Radilabstand der maximal radial äußeren und der radial inneren Radialposition des Begrenzungswandpunkts (26) mit minimalem Krümmungsradius und dem Axialabstand zwischen einem strömabwärtigen Ende (27) einer radial außen liegenden Gehäusewand (25) einer stromaufwärts des Übergangsströmungskanals (33) positionierten Turbinenkomponente (11) und der Vorderkante (16) der Stützrippen (15) bis zu 40% beträgt. Intermediate housing (14) according to claim 8, characterized in that a magnitude relationship between the Radilabstand the maximum radially outer and the radially inner radial position of the Begrenzungswandpunkts (26) with a minimum radius of curvature and the axial distance between a strömabwärtigen end (27) of a radially outer housing wall (25) one positioned upstream of the transition flow channel (33) Turbine component (11) and the front edge (16) of the support ribs (15) is up to 40%.
11. Zwischengehäuse (14) nach einem oder mehreren der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass das Verhältnis bis zu 5% beträgt. 11. intermediate housing (14) according to one or more of claims 1 to 8, characterized in that the ratio is up to 5%.
EP12716196.6A 2011-01-19 2012-01-16 Intermediate casing of a gas turbine engine comprising an outer boundary wall wich comprises upstream of a support strut a variable contour in circumferential direction in order to reduce secondary flow losses Active EP2665896B1 (en)

Applications Claiming Priority (2)

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DE102011008812A DE102011008812A1 (en) 2011-01-19 2011-01-19 intermediate housing
PCT/DE2012/000032 WO2012097798A1 (en) 2011-01-19 2012-01-16 Intermediate housing of a gas turbine with an outer bounding wall, having upstream of a supporting rib a contour that changes in the circumferential direction, for reducing secondary flow losses

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EP2665896B1 (en) 2015-06-10
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DE102011008812A1 (en) 2012-07-19
US9382806B2 (en) 2016-07-05

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