US20170211422A1 - Turbomachine with an insert device that can be arranged inside a recess of a wall - Google Patents

Turbomachine with an insert device that can be arranged inside a recess of a wall Download PDF

Info

Publication number
US20170211422A1
US20170211422A1 US15/411,327 US201715411327A US2017211422A1 US 20170211422 A1 US20170211422 A1 US 20170211422A1 US 201715411327 A US201715411327 A US 201715411327A US 2017211422 A1 US2017211422 A1 US 2017211422A1
Authority
US
United States
Prior art keywords
wall
insert device
insert
turbomachine
frame structure
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.)
Abandoned
Application number
US15/411,327
Other languages
English (en)
Inventor
Juergen BEIER
Patrick RUSS
Predrag Todorovic
Thomas Kubisch
Michael SCHACHT
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BEIER, JUERGEN, Ruß, Patrick, SCHACHT, MICHAEL, Kubisch, Thomas, TODOROVIC, PREDRAG
Publication of US20170211422A1 publication Critical patent/US20170211422A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a turbomachine with a wall that at least in certain areas extends circumferentially with respect to a central axis of the turbomachine, and with at least one insert device that can be connected at the wall in a releasable manner in the area of a recess that is arranged inside the wall according to the kind that is defined more closely in the generic term of claim 1 .
  • the wall In order to create an access area through the wall to an interior of the jet engine, the wall has a recess that can be closed with an insert plate, e.g. an access panel, wherein the insert plate is connected at the wall in a releasable manner at the circumferential side through a plurality of screws.
  • an insert plate e.g. an access panel
  • the insert plate In order to achieve a desired tightness against air leakage and to achieve a high degree of stability of the connection areas between the insert plate and the wall, the insert plate is held at the wall by a large number of screws that surround the insert plate at the circumferential edge.
  • this disadvantageously renders mounting or dismantling of such an insert plate laborious.
  • fire or flame resistance may possibly be achieved only in a very laborious manner.
  • turbomachine of the kind as it is mentioned above, in which an insert device can be brought into operative connection with the wall in the area of a recess in a simple and quick manner, wherein the connection area has a high stability and a tightness between the wall and the insert device during operation of the turbomachine is also improved.
  • this objective is achieved through a turbomachine with the features of the claim 1 .
  • a turbomachine having a wall that at least in certain areas extends circumferentially with respect to a central axis of the turbomachine and having at least one insert device that can be connected at the wall in a releasable manner in the area of a recess which is arranged inside the wall, wherein the insert device has a connection device by means of which the insert device can be brought into operative connection with a connection device of the wall.
  • connection device of the insert device has a projection that extends substantially in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device and that meshes in a groove of the connection device of the wall in the mounted state of the insert device, and wherein the connection device of the wall has a projection that in the mounted state of the insert device extends substantially in the radial direction of the turbomachine at least in certain areas and that meshes in a groove of the connection device of the insert device in the mounted state of the insert device.
  • the insert device can be brought into operative connection with the wall in the area of the recess in a simple and quick manner by means of a plug mechanism that is formed by the projections and grooves. Further, through the connection mechanism according to the invention, forces that are acting during operation of the turbomachine can be guided through the insert device, so that the insert device is included in the flow of forces of the wall.
  • the connection directions are in particular embodied so as to be substantially complementary to each other. Since the loads that are acting during operation of the turbomachine in the area of the wall can thus be transmitted through the insert device, the recess and the insert device can advantageously be embodied so as to be large, so that accessibility through the recess is improved.
  • connection device of the insert device coaction of the connection device of the insert device and the connection device of the wall by means of the coacting projections and grooves, a good sealing effect is created between the insert device and the wall, so that an air leakage is avoided in a particularly reliable manner during operation of the turbomachine.
  • connection devices through the coaction of the connection devices, a connection with a high fire or flame resistance is created between the insert device and the wall in a constructionally simple manner.
  • the projection of the wall extends substantially in an opposite direction with respect to an extension direction of the projection of the insert device that starts form a web-shaped area of the insert device.
  • the groove and the projection of the insert device and the wall are in particular arranged in an edge area of the insert device that is facing towards the wall or in an edge area of the wall that is facing towards the insert device, so that the connection device of the insert device forms a lateral end piece of the insert device and the connection device of the wall forms a lateral end piece of the wall.
  • the groove and the projection of the insert device and of the wall in particular extend substantially along the edge area of the insert device or along the edge area of the wall.
  • the projection of the insert device or of the wall has a surface that is also a surface of the groove of the insert device or of the wall.
  • the insert device can be brought in mesh with the wall in a simple manner if the projection of the insert device and the projection of the wall are embodied in such a manner that the insert device can be brought in mesh with the wall in a translational motion.
  • the wall and the insert device respectively have multiple projections and grooves, which in particular respectively extend along an edge area of the wall or of the insert device, and which are preferably arranged so as to adjoin each other in an alternating manner starting from an edge area of the insert device or of the wall in the direction of the central area of the insert device or in a direction opposite thereto.
  • the grooves and the projections of the insert device and the grooves and the projections of the wall form a wave-shaped or a jagged profile in the cross-section.
  • connection device of the insert device and/or the connection device of the wall can also have one or multiple areas which only partially run along the circumference of the respective edge area.
  • the insert device can be retained at the wall in the area of the recess in the mounted position of the insert device by at least one attachment means.
  • the attachment means which can for example be embodied as screws, can for example act together with respectively one female thread, which is preferably arranged so as to be substantially flush with a surface of the insert device that is arranged so as to be facing inward in the radial direction in the mounted position of the insert device.
  • the insert device has a handle-like element at a side that is located radially outside in mounted position of the insert device.
  • the insert device and the wall have a comparable and in particular identical structure in the cross-section, and are preferably embodied respectively with a sound-absorbing middle layer, an inner layer and an outer layer.
  • the inner layer as well as the outer layer can respectively be embodied in a multi-layer manner, wherein the respective layers are in particular embodied with a composite material, a metal, for example aluminum, or with carbon, and are for example perforated.
  • the respective layer can for example be embodied as an injection-molded part.
  • connection device of the insert device and/or the connection device of the wall is or are formed by the middle layer and/or the outer layer and/or the inner layer of the wall or of the insert device.
  • the insert device delimits a flow channel on a side that is internal with respect to the radial direction of the turbomachine and the projection of the insert device is connected to a web of the insert device that, in the mounted position of the insert device, is arranged on a side of a web of the wall that is internal with respect to the radial direction of the turbomachine and via which the projection is connected to the wall, the insert device is advantageously retained in its position in which it is acting together with the wall through a pressure that is acting in the area of the flow channel during operation of the turbomachine.
  • the web of the insert device is arranged on a side of the web of the wall that is exterior with respect to the radial direction of the turbomachine.
  • the wall has a frame structure that forms multiple recesses, wherein multiple insert devices are provided, which respectively have a frame that substantially corresponds to a shape of the recess of the frame structure, and wherein each insert device can be brought into operative connection with the frame structure in the area of a recess in a releasable manner.
  • the recesses formed by the frame structure can have any shape.
  • the wall can also be embodied without a frame structure, for example with recesses that are substantially shaped in a rectangular, oval, elliptical or otherwise shaped manner.
  • the recesses of the frame structure that is in particular embodied with rod-shaped elements and the insert devices that are in particular embodied in a plate-shaped manner are configured so as to be triangle-shaped, the guiding of all forces that are acting at the wall during operation of the turbomachine are improved by the insert devices.
  • Loads that act in the area of the wall during operation of the turbomachine can advantageously be guided through the insert devices and the frame structure of the wall in all orientations, i.e. also if they act obliquely with respect to the longitudinal direction and/or the circumferential direction of the turbomachine.
  • the recesses or maintenance openings can be advantageously embodied so as to be large, without the flow of forces being negatively impacted in the area of the wall. In this manner, all areas of the turbomachine that have to be reached through the recesses can be made accessible already with a small number of recesses.
  • comparatively large recesses can advantageously be provided even in the turbomachines that are embodied in a small manner, so that accessibility of areas located inside the recesses, such as for example a core engine, is improved, for example for maintenance purposes for a worker. Accessibility of the inner areas is in particular improved when the frame structure comprises multiple insert devices that are embodied in a modular manner.
  • the recesses of the frame structure can also be embodied in a hexagon-shaped and/or octagon-shaped manner, wherein the recesses can be brought into operative connection with insert devices that are correspondingly embodied in a hexagon-shaped and/or octagon-shaped manner.
  • the frame structure in particular represents a skeleton-like, load-bearing structure that is preferably formed by multiple straight or bent rod-shaped elements that are connected to each other.
  • the frame structure can form a spatial frame, a so-called space frame, or a framework structure, a so-called truss structure.
  • the frame structure of the wall completely surrounds the axial area of the turbomachine in the circumferential direction of the turbomachine, and that preferably in all recesses formed by the frame structure insert devices can be arranged that can be released independently from each other, preferably insert devices that are embodied in a modular manner.
  • a closed sleeve is formed in the circumferential direction of the turbomachine.
  • the guiding of forces which occur during operation of the turbomachine is improved due to the fact that the frame structure forms exclusively triangle-shaped recesses, with which respectively one insert device can be brought in operative connection in a releasable manner.
  • each insert device can be connected to the frame structure in the area of any recess of the frame structure, and insert devices can be switched in a simple manner if necessary.
  • the frame structure has two ring-shaped frame elements that are arranged at a distance from each other in the longitudinal direction of the turbomachine, wherein respectively one corner point of a recess is assigned to a ring-shaped frame element of the frame structure, and two corner points of the recess are assigned to the other ring-shaped frame element of the frame structure.
  • the two corner points of a recess that are assigned to the ring-shaped frame element of the frame structure are arranged in a mirror-symmetrical manner with respect to a straight line that runs through the corner point that is assigned to the other ring-shaped frame element of the frame structure in the longitudinal direction of the turbomachine, wherein the recesses preferably form isosceles triangles.
  • the frame structure can have a large extension in the longitudinal direction of the turbomachine in a simple and stable manner.
  • a retention device is arranged for external connection of the turbomachine in the area of a ring-shaped frame element of the frame structure.
  • forces that act during operation of the turbomachine can advantageously be transmitted via the retention device.
  • the retention device is arranged in an area of the second ring-shaped frame element, which is assigned multiple, in particular six, corner points of different recesses of the frame structure, a retention of the turbomachine is possible for example in an area of the frame structure that is central with respect to the longitudinal direction of the turbomachine.
  • the provision of the frame structure with multiple ring-shaped frame elements thus facilitates a flexible arrangement of the retention device in the longitudinal direction of the turbomachine.
  • the wall that comprises the frame structure and the insert devices circumferentially surrounds or encloses a flow channel, in particular a bypass channel or a core flow channel of a turbomachine that is in particular embodied as a jet engine. If the wall delimits the bypass channel externally with respect to the radial direction, by removing the respective insert device, an access to a desired area of the core engine can be facilitated in a simple manner through the thus opened recess, for example for maintenance work.
  • the insert devices can be made available in a simple manner with the respective constructional units, so that the insert devices can be mounted at the frame structure in one mounting step together with the respective constructional unit.
  • additional constructional units can be arranged at the frame structure in a simple manner without any elaborate modification of the frame structure.
  • the constructional unit can for example be a surface cooler, wherein the constructional unit is preferably arranged at the side of the insert device that is facing away from the flow channel in the mounted state of the insert device.
  • the insert devices can advantageously be embodied without fastening devices for the constructional units that are to be attached at the wall if the frame structure has connection points for connecting the constructional units.
  • FIG. 1 shows a strongly schematized longitudinal section of a jet engine with a bypass channel which is delimited by a wall at the exterior side;
  • FIG. 2 shows a simplified view of a part of the jet engine according to FIG. 1 , wherein a frame structure of the wall can be seen in more detail;
  • FIG. 3 shows a simplified three-dimensional rendering of a section of the jet engine according to FIG. 2 , wherein plate-shaped insert devices are respectively inserted inside recesses that are formed by the frame structure, and wherein a retention device is arranged at a downstream ring-shaped frame element of the frame structure for connecting the jet engine to an aircraft;
  • FIG. 4 shows a rendering of the jet engine that substantially corresponds to FIG. 3 , wherein a retention device is arranged at a central one of three ring-shaped frame elements of the frame structure for connecting the jet engine to an aircraft;
  • FIGS. 5-7 show simplified renderings of a section of the jet engine according to FIG. 1 to FIG. 4 ;
  • FIG. 8 shows a simplified rendering of a frame structure of the wall of the jet engine according to FIG. 1 in isolation
  • FIG. 9 shows a schematic three-dimensional view of multiple insert devices in isolation, which are provided for acting together with the frame structure according to FIG. 8 ;
  • FIGS. 10-13 show simplified three-dimensional views of a section of the wall of the jet engine according to FIG. 1 , wherein an insert device is embodied with a connection device that can be brought into operative connection with a connection device of the wall in the area of a recess of the wall;
  • FIGS. 14-16 show three-dimensional views of a section of the wall of the jet engine according to FIG. 1 , wherein an insert device is shown with a further embodiment of a connection device that can be brought into operative connection with a connection device of the wall in the area of a recess of the wall;
  • FIG. 17 shows a strongly simplified rendering of a structure of the wall and of the insert device according to one of FIGS. 1 to 16 ;
  • FIG. 18 shows a strongly simplified sectional rendering of a section of the wall of the jet engine according to FIG. 1 , wherein an insert device can be brought into operative connection with a connection device of the wall by means of an alternatively embodied connection device;
  • FIGS. 19, 20 show strongly simplified renderings of different embodiments of the connection device of the insert device and of the connection device of the wall according to FIG. 18 ;
  • FIG. 21 shows a strongly simplified rendering of an alternatively embodied wall of the bypass channel of the jet engine according to FIG. 1 , wherein the wall is embodied with four recesses that can respectively be closed with an insert device.
  • FIG. 1 shows a continuous-flow machine or a turbomachine that is embodied as a jet engine 10 in which the invention can be used.
  • the invention can also be used with different turbomachines.
  • the jet engine or aircraft engine 10 is configured in a conventional manner and comprises, arranged successively in flow direction A, an air inlet 11 , a fan 12 that rotates inside a housing, an intermediate pressure compressor 13 , a high pressure compressor 14 , combustion chambers 15 , a high pressure turbine 16 , an intermediate pressure turbine 17 and a low-pressure turbine 18 as well as an exhaust nozzle 19 , which are all arranged around a central engine axis 1 .
  • the intermediate pressure compressor 13 and the high pressure compressor 14 respectively comprise multiple stages, of which each has an arrangement of fixedly arranged stationary guide blades/vanes 20 that extend in the circumferential direction and are generally referred to as stator blades/vanes and which project radially inward from the engine shroud 21 through the compressors 13 , 14 into a ring-shaped flow channel or core flow channel 31 .
  • the compressors have an arrangement of compressor rotor blades/vanes 22 that project radially outward from a rotatable drum or disc 26 and which are coupled to hubs 27 of the high pressure turbine 16 or the intermediate pressure turbine 17 .
  • the turbine sections 16 , 17 , 18 have similar stages, comprising an arrangement of stationary guide blades/vanes 23 projecting radially inward from the housing 21 through the turbines 16 , 17 , 18 into the ring-shaped core flow channel 31 , and a subsequent arrangement of turbine blades/vanes 24 projecting outwards from the rotatable hub 27 .
  • the compressor drum or compressor disc 26 and the blades/vanes 22 arranged thereon as well as the turbine rotor hub 27 and the turbine rotor blades/vanes 24 arranged thereon rotate around the engine axis 1 .
  • the reference sign 28 indicates an outlet cone.
  • the fluid flow that is supplied to the jet engine through the air inlet 11 is divided into a bypass flow and a core flow, wherein the bypass flow flows through a bypass channel 30 that is embodied in a cylindrical or conical manner, and the core flow flows into the engine core or core flow channel 31 .
  • the bypass channel 30 as well as the core flow channel 31 are delimited by a wall 32 , 33 , 34 , 35 at least in certain areas in the flow direction A at a side that is interior and a side that is exterior with respect to the radial direction R of the jet engine 10 .
  • the wall 32 that is delimiting the bypass channel 30 on the radially exterior side is discussed in more detail, wherein the walls 33 , 34 , 35 can in principle be embodied in a way comparable to the wall 32 .
  • FIG. 2 to FIG. 4 respectively show a section of the jet engine 10 , wherein the wall 32 can be seen in more detail.
  • the wall 32 is embodied with a skeleton-like frame structure 36 that forms a load-bearing structure.
  • the frame structure 36 has three ring-shaped frame elements 37 , 38 , 39 that are arranged at a distance from each other in the flow direction A, wherein in the present case a distance in flow direction A between the first ring-shaped frame element 37 and the second ring-shaped frame element 38 corresponds to a distance between the second ring-shaped frame element 38 and the third ring-shaped frame element 39 .
  • the first ring-shaped frame element 37 and the second ring-shaped frame element 38 as well as the second ring-shaped frame element 38 and the third ring-shaped frame element 39 are connected to each other respectively by a plurality of further frame elements 40 that are embodied in a rod-shaped manner.
  • only triangle-shaped recesses 42 are formed by the ring-shaped frame elements 37 , 38 , 39 and the further frame elements 40 , wherein respectively a first corner point 44 of the triangular recesses 42 is assigned to a ring-shaped frame element 37 or 38 or 39 , and the other two corner points 45 , 46 of the recess 42 are assigned to a neighboring ring-shaped frame element 37 or 38 or 39 .
  • the two further corner points 45 and 46 are arranged in a mirror-symmetrical manner in all recesses 42 with respect to a straight line that runs through the first corner point 44 in the flow direction A, with the recesses 42 preferably forming isosceles triangles.
  • the wall 32 further has a plurality of plate-shaped insert devices 48 which are shown in FIG. 3 and FIG. 4 and which are configured with a substantially identical shape and can respectively be brought into operative connection with the frame structure 36 in a releasable manner in the area of a recess 42 . Due to the fact that the insert devices 48 are embodied with substantially the same shape, in the present case each insert device 48 can be brought into operative connection with the frame structure 36 in the area of each recess 42 .
  • the insert devices 48 are respectively embodied so as to be bent in the circumferential direction U.
  • FIG. 3 shows, in a strongly schematized manner, an insert device 49 that is connected to a constructional unit, which here is embodied as a surface cooler 51 , on a side that is facing away from the bypass channel 30 .
  • the insert device 49 can be pre-assembled in a simple manner together with the surface cooler 51 and can be arranged at the frame structure 36 in one work step together with the surface cooler 51 .
  • FIG. 3 What can further be seen in FIG. 3 is a retention device 53 that is arranged in the area of the third ring-shaped frame element 39 and that is provided for connecting the jet engine 10 at an aircraft.
  • the third ring-shaped frame element 39 is arranged substantially in the same cross-sectional plane of the jet engine 10 as the so-called A-Frames 59 .
  • a retention device 54 for connecting the jet engine 10 at an aircraft is connected to the second ring-shaped frame element 38 in an area to which six corner points of adjoining recesses 42 are assigned in the present case.
  • loads that are occurring during operation of the jet engine 10 can be transferred in an advantageous manner to the A-frames 59 that are arranged in the area of the third ring-shaped frame element 39 via the further frame elements 40 that are indicated by arrows 56 and 57 .
  • FIG. 5 to FIG. 11 again respectively show a part of the jet engine 10 , wherein in the present case the wall 32 has a frame structure 61 that is embodied with two ring-shaped frame elements 37 , 38 . Further frame elements 40 in turn connect the ring-shaped frame elements 37 , 38 in such a manner that circumferentially distributed triangle-shaped recesses 42 are formed, which are embodied in a substantially identical manner in the present case.
  • an insert device 50 is coupled to a pre-cooling device 52 , which can be brought into operative connection with the frame structure 61 in a simple manner on a first side of the jet engine 10 as well as on a second side of the jet engine 10 which is arranged opposite the first side, for example.
  • the pre-cooling device 52 can have a flap device 55 through which air can be extracted from the bypass channel 30 to a desired amount during operation of the jet engine 10 .
  • an actuator 58 that actuates the flap device 55 can advantageously be arranged with the insert device 50 on a side of the wall 32 that is facing away from the bypass channel 30 .
  • the frame structure can also have four or more ring-shaped frame elements, which in particular can be connected to further frame elements in the manner more closely described above, wherein respectively one insert device can be inserted into recesses formed by the frame structure and can be brought into operative connection with the frame structure.
  • the insert devices 48 that are shown in isolation in FIG. 9 can be brought into operative connection with the frame structure 61 that is shown in isolation in FIG. 8 , as will be described more closely in the following.
  • the insert devices 48 , 49 , 50 can also be brought into operative connection with the frame structure 36 in the area of the recesses 42 .
  • the insert device 48 has a connection device 64 which can be seen in more detail in FIG. 10 to FIG. 13 , and which here is embodied so as to completely surround the insert device in the area of an edge area 67 of the insert device 48 that is facing towards the frame structure 61 .
  • the frame structure 61 is configured with a connection device 65 that is arranged in the edge area 68 of the frame elements 37 to 40 of the frame structure 61 that is facing towards the insert device 48 , wherein in the present case the connection device 65 of the frame structure 61 is embodied so as to run along the entire edge area 68 .
  • connection device 64 has a web 71 which, starting from a central central area 70 of the insert device 48 , is arranged in an area that is facing towards the bypass channel 30 in the mounted position of the insert device 48 , and which is embodied with a substantially V-shaped or U-shaped projection 72 or protrusion that extends substantially outwards with respect to the radial direction R on a side that is facing away from the central area 70 .
  • a V-shaped or U-shaped groove 73 that is open substantially outwards with respect to the radial direction R is formed by the projection 72 , the web 71 , and the central area 70 , wherein a surface 74 , which is facing towards the central area 70 and is substantially rectilinear in the radial direction R in the shown cross-section, represents a part of the projection 72 as well as part of the groove 73 .
  • connection device 65 of the frame structure 61 is embodied in a substantially mirror-symmetrical manner with respect to the connection device 64 of the insert device 48 , and also has a projection 77 or a protrusion, which here is connected via a web 79 to a central area 78 of the frame element 40 , so that the projection 77 is connected to the web 79 on a side of the web 79 that is facing away from the central area 78 .
  • the web 79 is in turn arranged in an area of the frame element 40 that is facing away from the bypass channel 30 in mounted position of the insert device 48 .
  • the projection 77 extends substantially inward in the radial direction R starting from the web 79 and is embodied in a substantially V-shaped or U-shaped manner.
  • a V-shaped or U-shaped groove 80 is formed by the projection 77 , the web 79 and the central area 78 of the frame element 37 to 40 , opening substantially inward in the radial direction R.
  • a surface 81 that is facing towards the central area 78 and that is substantially rectilinear in the radial direction R in the shown cross-section is part of the projection 77 as well as part of the groove 80 .
  • the insert device 48 and the frame elements 37 , 38 , 39 , 40 of the frame structure 61 have a substantially comparable structure and are embodied with an inner layer 94 , a middle or intermediate layer 95 , and an outer layer 96 .
  • the inner layer 94 and the outer layer 96 are configured with a metallic material, whereas the middle layer 95 is embodied with a sound-absorbing material.
  • the inner layer 94 and the outer layer 96 can have multiple, for example perforated, layers 97 or 98 .
  • the structure of the insert device 48 and the frame structure 61 are chosen in such a manner that the insert devices 48 and the frame structure 61 can reliably withstand loads that occur during operation of the jet engine 10 , and that a side of the wall 32 that is facing away from the bypass channel 30 is secured against potential entry of fire and is separated in an airtight manner from the bypass channel 30 to the desired degree.
  • the grooves 73 or 80 and the projections 72 or 77 of the insert device 48 and of the frame element 40 are an integral part of the middle layer 95 only.
  • the insert device 48 and the frame structure 61 in particular act together via the surfaces 74 and 81 , wherein here the surfaces 74 and 81 act together in the cross-section along a line of contact K according to FIG. 11 .
  • the projection 72 abuts a surface 105 of the groove 80 of the frame structure 61 , which is arranged on a side of the surface 74 that is facing towards the central area 78 of the frame structure 61 , with a surface 75 that is facing towards a central area 78 of the frame structure 61 .
  • the projection 77 of the frame structure 61 also abuts a surface 104 of the groove 73 of the insert device 48 with a surface 82 that is arranged on a side of the surface 81 that is facing towards the central area 70 of the insert device 48 , wherein a top area of the projections 72 or 77 is respectively arranged at a distance from the groove base of the groove 80 or the groove 73 .
  • the surfaces 74 and 81 that are formed by a substantially planar line in the cross-section are in total preferably embodied in a conical manner, wherein the line of contact K, which is defined by a surface vector that is arranged perpendicular to a surface normal of the surfaces 74 and 81 , in the present case together with the radial direction R encloses an angle 83 in the area of the line of contact K.
  • the angle 83 is preferably constant along the entire edge area 67 of the insert device 48 .
  • an area of the surfaces 74 and 81 that is external with respect to the radial direction R extends further in the direction of the central area 70 of the insert device 48 than an area of the surfaces 74 and 81 that is internal with respect to the radial direction R.
  • a force that substantially acts in the direction of the central area 70 of the insert device 48 is induced on the insert device 48 and a force that is substantially opposite hereto is induced in the frame structure 61 through forces that act on the insert device 48 and the frame structure 61 during operation of the jet engine 10 , so that the insert device 48 is retained securely at the frame structure 61 .
  • a sealing effect between the insert device 48 and the frame structure 61 is also improved in this way.
  • the insert device 48 that is embodied so as to be substantially concentric to the engine axis 1 in the circumferential direction U, as is indicated by reference sign D in FIGS. 10 to FIG. 13 , can be brought from the side of the frame structure 61 that is internal with respect to the radial direction R into the position where it is connected to the frame elements 37 to 40 shown in FIG. 10 , FIG. 11 and FIG. 13 in a translational mounting motion starting from the position shown in FIG. 12 .
  • the mounting direction or dismantling direction D extends substantially in the direction of an angle bisector of the surfaces 81 and 105 and the surfaces 74 and 104 , which in the present case are arranged so as to be substantially parallel to each other.
  • the angle 84 is provided for manufacturing-related reasons and, for another thing, in order to avoid any blocking of parts during dismantling of the insert device 48 in a simple manner.
  • the angle bisectors of the surfaces 81 and 105 or of the surfaces 74 and 104 are substantially oriented in the mounting or dismantling direction D in every circumferential area of the insert device 48 , so that mounting as well as dismantling of the insert device 48 can be performed in a simple manner.
  • a handle element that is not shown in any more detail can be arranged on the side of the insert device 48 that is facing away from the bypass channel 30 .
  • a higher pressure is applied to the side of the wall 32 that is facing towards the bypass channel 30 than to a side of the wall 32 that is facing away from the bypass channel 30 .
  • a force that substantially acts outwards with respect to the radial direction R is applied to the wall 32 . Due to the angled arrangement of the surfaces 74 and 81 with respect to the radial direction R, these forces are transformed into a force that acts in the circumferential direction U and that retains the insert device 48 at the frame structure 61 . Further, the insert device 48 and the frame structure 61 are widened during operation of the jet engine 10 due to the high rotational speeds.
  • the insert device 48 is secured in the mounted position through attachment means that are for example embodied as screws 85 .
  • attachment means that are for example embodied as screws 85 .
  • bores 87 , 88 that substantially extend in the radial direction R are provided in the edge area 67 of the insert device 48 and in the edge area 68 of the frame structure 61 , being arranged so as to be concentric and aligned with each other in the mounted state of the insert device 48 .
  • nuts 89 are presently inserted into the bores 87 of the insert device 48 , with the nuts 89 being arranged so as to be flush with a surface of the insert device 48 which is oriented in the direction of the bypass channel 30 .
  • screws 85 can be guided through the bores 87 and 88 and can be brought into operative connection with the nuts 89 from the outside with respect to the radial direction R.
  • the insert device 48 that is shown in FIGS. 14 to 16 is configured with a connection device 101 that is embodied in an alternative manner to the connection device 64 .
  • the frame structure 61 is embodied with a connection device 102 that is embodied in an alternative manner to the connection device 65 , wherein in the following only the differences of the connection devices 101 or 102 to the connection device 64 or 65 will be discussed.
  • connection device 101 of the insert device 48 differs from the connection device 64 of the insert device 48 substantially in the fact that the groove 73 and the projection 72 form a wave-shaped surface and the surface 74 extends further in the direction of the central area 78 of the frame structure 61 with an area that is external with respect to the radial direction R than with an area that is internal with respect to the radial direction R. Further, surface 104 of the groove 73 that is facing towards the central area 70 of the insert device 48 is formed by the outer layer 96 , which in the edge area 67 extends obliquely inwards in the radial direction R in the mounted position of the insert device 48 .
  • connection device 102 of the frame structure 61 is embodied in a substantially mirror-symmetrical or complementary manner to the connection device 101 of the insert device 48 .
  • the projection 77 and the groove 80 are also embodied with a wave-shaped surface.
  • the surface 81 extends further in the direction of the central area 70 of the frame structure 61 with an area that is external with respect to the radial direction R than with an area that is internal with respect to the radial direction R.
  • the surface 105 of the groove 80 that is facing towards the central area 78 of the frame structure 61 is formed by the inner layer 96 of the frame structure 61 that extends obliquely outwards in the radial direction R in the edge area 68 .
  • bores 106 , 107 are provided that are distributed circumferentially with respect to the respective edge areas 67 , 68 and that are arranged in an aligned and concentric manner with respect to each other in the mounted state of the insert device 48 , wherein the insert device 48 and the frame structure 61 can be connected to each other in a releasable manner by means of an attachment means that is embodied as a screw 109 .
  • FIG. 18 to FIG. 20 show another alternatively embodied connection device 115 of the insert device and an alternatively embodied connection device 116 of the frame structure 61 in a strongly schematized rendering.
  • the connection device 115 as well as the connection device 116 are formed exclusively by the inner layer 94 of the insert device 46 or the frame structure 61 .
  • connection device 115 of the insert device 48 extends in a direction that is oriented away from the central area 70 of the insert device 48 and in cross-section has multiple, in the present case four, projections 118 that are arranged next to each other and that in the present case can be respectively embodied in a manner comparable to the projection 72 .
  • Grooves 119 are respectively formed between neighboring projections 118 , which in turn can be embodied in a manner substantially comparable to the groove 73 .
  • connection device 116 of the frame structure 61 is embodied so as to be at least approximately complementary to the connection device 115 and also has four projections 121 and four grooves 122 , which in turn can be embodied in a manner comparable to the projection 77 or the groove 80 .
  • the connection device 115 as well as the connection device 116 can have a wave-shaped profile that is shown in FIG. 19 in a strongly schematized manner as well as a jagged profile that is shown in FIG. 20 in a strongly schematized manner.
  • a friction coefficient between the insert device 48 and the frame structure 61 is advantageously large due to a coaction of the connection devices 115 and 116 , so that a sealing effect between the insert device 48 and the frame structure 61 is also high during operation of the jet engine 10 , and only a small number of attachment means, which are indicated in a schematic manner and can for example be embodied as bolts 124 , is necessary for connecting the insert device 48 to the frame structure 61 . Further, through the configuration of the connection devices 115 and 116 exclusively by the inner layer 94 , the structure is not affected or affected only to a small extent, so that the middle layer 95 has a particularly good sound-absorbing effect.
  • the locking device is embodied as a separate structural component and is in particular connected to a middle layer of the frame structure, for example by means of bonding or another fixating method.
  • FIG. 21 shows a wall 140 that is embodied in an alternative manner to wall 32 and does not have a frame structure, and which in the present case is configured with four oval or elliptical recesses 141 that are embodied with the same shape.
  • insert devices which cannot be seen in any more detail can be inserted, wherein the insert devices can be brought into operative connection with the wall in the manner described more closely above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US15/411,327 2016-01-22 2017-01-20 Turbomachine with an insert device that can be arranged inside a recess of a wall Abandoned US20170211422A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016101168.1A DE102016101168A1 (de) 2016-01-22 2016-01-22 Strömungsmaschine mit einer in einer Ausnehmung einer Wandung anordenbaren Einsetzeinrichtung
DE102016101168.1 2016-01-22

Publications (1)

Publication Number Publication Date
US20170211422A1 true US20170211422A1 (en) 2017-07-27

Family

ID=57539057

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/411,327 Abandoned US20170211422A1 (en) 2016-01-22 2017-01-20 Turbomachine with an insert device that can be arranged inside a recess of a wall

Country Status (3)

Country Link
US (1) US20170211422A1 (de)
EP (1) EP3196427B1 (de)
DE (1) DE102016101168A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220111950A1 (en) * 2020-10-14 2022-04-14 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Ducted fan of an aircraft and aircraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11215054B2 (en) 2019-10-30 2022-01-04 Raytheon Technologies Corporation Airfoil with encapsulating sheath
US11466576B2 (en) * 2019-11-04 2022-10-11 Raytheon Technologies Corporation Airfoil with continuous stiffness joint

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5076514A (en) * 1990-08-03 1991-12-31 The Boeing Company Apparatus for latching two parts together
US20020006078A1 (en) * 2000-06-28 2002-01-17 Massimo Battini Sound-absorbing and reinforcing structure for engine nacelle acoustic panel
US20080072572A1 (en) * 2006-09-20 2008-03-27 Snecma Turbomachine fan duct
US7435050B2 (en) * 2006-01-11 2008-10-14 United Technologies Corporation Split flange V-groove and anti-rotation mating system
US8272203B2 (en) * 2007-07-26 2012-09-25 Snecma External fan duct casing in a turbomachine
US20180245515A1 (en) * 2017-02-24 2018-08-30 Mra Systems, Llc Acoustic liner having multiple layers

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2661213B1 (fr) * 1990-04-19 1992-07-03 Snecma Moteur d'aviation a tres grand taux de dilution et du type dit contrafan avant.
GB9120658D0 (en) * 1991-09-27 1991-11-06 Short Brothers Plc Ducted fan turbine engine
FR2920137B1 (fr) * 2007-08-20 2009-09-18 Aircelle Sa Fixation d'une structure d'une nacelle de turboreacteur par bride couteau/gorge renforcee
US9643392B2 (en) * 2013-07-29 2017-05-09 The Boeing Company Septumization of honeycomb sandwiches

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5076514A (en) * 1990-08-03 1991-12-31 The Boeing Company Apparatus for latching two parts together
US20020006078A1 (en) * 2000-06-28 2002-01-17 Massimo Battini Sound-absorbing and reinforcing structure for engine nacelle acoustic panel
US7435050B2 (en) * 2006-01-11 2008-10-14 United Technologies Corporation Split flange V-groove and anti-rotation mating system
US20080072572A1 (en) * 2006-09-20 2008-03-27 Snecma Turbomachine fan duct
US8272203B2 (en) * 2007-07-26 2012-09-25 Snecma External fan duct casing in a turbomachine
US20180245515A1 (en) * 2017-02-24 2018-08-30 Mra Systems, Llc Acoustic liner having multiple layers

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220111950A1 (en) * 2020-10-14 2022-04-14 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Ducted fan of an aircraft and aircraft
US11541989B2 (en) * 2020-10-14 2023-01-03 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Ducted fan of an aircraft and aircraft

Also Published As

Publication number Publication date
DE102016101168A1 (de) 2017-07-27
EP3196427A1 (de) 2017-07-26
EP3196427B1 (de) 2019-03-20

Similar Documents

Publication Publication Date Title
US9097141B2 (en) Axial bolting arrangement for mid turbine frame
US10132194B2 (en) Seal segment low pressure cooling protection system
EP2098686B1 (de) Doppelwellen-Gasturbine
US9328926B2 (en) Segmented combustion chamber head
EP1739284B1 (de) Gasturbine mit Adapter zur Ermöglichung einer Inspektion mit einem Endoskop
EP1947298B1 (de) Schieberdichtungssatz für Gasturbinentriebwerke
US9334738B2 (en) Gas turbine including belly band seal anti-rotation device
US20170211422A1 (en) Turbomachine with an insert device that can be arranged inside a recess of a wall
CN104154042B (zh) 用于轴流式涡轮机的抽气系统
US10301957B2 (en) Pinned seal
RU2704572C2 (ru) Вращающийся узел авиационного газотурбинного двигателя, вентилятор авиационного газотурбинного двигателя, содержащий такой узел, и способ монтажа этого узла
EP2977617B1 (de) Abblasventil mit im verschlussorgan integrierter resonanzkammer
US9951654B2 (en) Stator blade sector for an axial turbomachine with a dual means of fixing
EP2249003B1 (de) Gasturbine
WO2020066891A1 (ja) 蒸気タービンの排気室、蒸気タービン及び蒸気タービンの換装方法
WO2015064502A1 (ja) ナット及び回転機械
US9366185B2 (en) Flexible connection between a wall and a case of a turbine engine
US10641115B2 (en) Segmented conduit with airfoil geometry
US10480333B2 (en) Turbine blade including balanced mateface condition
US20160215636A1 (en) Turbine bucket for control of wheelspace purge air
KR20140124359A (ko) 터보차저
EP3379150B1 (de) Gasturbine
EP2846048B1 (de) Flussablenkungsanordnung
US11603775B2 (en) Removable pin on a turbomachine nozzle
US10584612B2 (en) Ventilated bush

Legal Events

Date Code Title Description
AS Assignment

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BEIER, JUERGEN;KUBISCH, THOMAS;RUSS, PATRICK;AND OTHERS;SIGNING DATES FROM 20161220 TO 20170105;REEL/FRAME:041027/0202

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION