US20200217214A1 - Rim seal - Google Patents
Rim seal Download PDFInfo
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- US20200217214A1 US20200217214A1 US16/825,031 US202016825031A US2020217214A1 US 20200217214 A1 US20200217214 A1 US 20200217214A1 US 202016825031 A US202016825031 A US 202016825031A US 2020217214 A1 US2020217214 A1 US 2020217214A1
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- Prior art keywords
- rotor
- stator
- axial
- platforms
- rim
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- 230000004323 axial length Effects 0.000 claims abstract description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 24
- 238000000034 method Methods 0.000 claims description 22
- 239000007789 gas Substances 0.000 description 29
- 230000003068 static effect Effects 0.000 description 7
- 239000003570 air Substances 0.000 description 5
- 239000000567 combustion gas Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000009420 retrofitting Methods 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- the application relates generally to gas turbine engines and, more particularly, to a rim seal between a bladed rotor and an adjacent non-rotating structure in gas turbine engines.
- Compressors and turbines of a gas turbine engine generally have a plurality of stators and rotors in sequential disposition along a rotational axis.
- the rotating elements such as compressor rotors and turbine rotors, operate at a very high rotation speed, and are mounted adjacent to and/or between non-rotating structures, such as stators, within the engine.
- These non-rotating structures are designed to be as close as possible to the rotating blade platforms, in order to mitigate pressurized gas ingestion inside the gas turbine engine.
- a rim seal arrangement is provided between the blade platforms of the rotor and the adjacent non-rotating structure in order to further limit losses from the main gas path.
- a rim seal arrangement for a gas turbine engine comprising: a rotor having a rotor disk adapted to rotate about a longitudinal axis and a plurality of rotor blades circumferentially spaced apart about the rotor disk, the rotor disk defining an axial centerline plane at a midpoint between opposed upstream and downstream faces of the rotor disk at a radial outer rim of the rotor disk, each of the rotor blades including a rotor platform mounted to the rotor disk and an airfoil extending radially from the rotor platform to project within a main gas path of the gas turbine engine; a stator disposed adjacent to and axially spaced apart from the rotor, the stator including a plurality of vanes radially extending through the main gas path between a stator platform at a radially inner end and an outer shroud at a radially outer end; each of the rotor platforms including a rotor flange project
- a rim seal arrangement for a gas turbine engine comprising: a rotor including a set of rotating blades having blade platforms mounted to a rotor disk, a non-rotating structure disposed adjacent to and downstream of the rotor and axially spaced apart therefrom to define an annular space between the blade platforms and the adjacent non-rotating structure, and a rim seal formed between the non-rotating structure and the blade platforms of the rotor and extending through the annular space, the rim seal including an annular rotor rim extending downstream from the blade platforms towards the non-rotating structure and an annular static rim extending axially upstream from the non-rotating structure towards the rotor, the annular rotor rim being radially offset from the annular static rim by a radial gap distance, and the annular static rim and the annular rotor rim axially overlapping each other by an axial overlap distance, and a trench defined in the blade platforms adjacent to and in radial alignment with the
- a method of forming a rim seal between a rotor and a stator in a turbine of a gas turbine engine the stator being axially spaced apart from the rotor immediately downstream therefrom, the rotor including a set of turbine blades having blade platforms mounted to a rotor disk rotatable about a longitudinal axis
- the method comprising: providing the rim seal between an annular rotor rim extending axially downstream from the blade platforms of the rotor and an annular stator rim extending axially upstream from the stator, the annular stator rim and the annular rotor rim axially overlapping each other by an axial overlap distance, and the annular stator rim and the annular rotor rim being radially offset by a radial gap distance; increasing the axial overlap distance by increasing an axial length of the annular stator rim; and forming a trench in the blade platforms of the rotor to accommodate the increased axial length of annular stator
- a method of forming a rim seal between a rotor and a stator of a gas turbine engine comprising: obtaining a rotor having a rotor disk rotatable about a longitudinal axis and having rotor blades protruding from rotor platforms, the rotor blades located radially outwardly of the rotor disk; obtaining a stator having vanes protruding from stator platforms; moving the rotor and the stator toward one another in an axial direction relative to the longitudinal axis until rotor flanges defined by the rotor platforms axially overlap stator flanges defined by the stator platforms; and further moving the rotor and stator toward one another in the axial direction to decrease an axial distance between ends of the stator platforms and bases of trenches defined by the rotor platforms, the bases of the trenches located axially closer to an axial centerline plane of the rotor disk than are upstream and downstream faces of the rotor
- FIG. 1 is a schematic cross-sectional view of a gas turbine engine
- FIG. 2 a is a cross-sectional view of a portion of a turbine of the gas turbine engine of FIG. 1 ;
- FIG. 2 b is an enlarged view of a portion of the cross-sectional view of FIG. 2 a;
- FIG. 3 a is another cross-sectional view of a portion of a turbine of the gas turbine engine of FIG. 1 ;
- FIG. 3 b is an enlarged view of a portion of the cross-sectional view of FIG. 3 a.
- FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
- the fan 12 , the compressor 14 , and the turbine section 18 are mounted on at least one shaft 15 .
- Each of the compressor section 14 and the turbine section 18 includes rotating elements, namely compressor rotors and turbine rotors, and static or non-rotating structures, including compressor stators and turbine stators.
- a rim seal 45 is disposed between one or more of these rotors and an adjacent non-rotating structure, such as a stator.
- the turbine section 18 includes an axial turbine comprising a turbine rotor 22 and a turbine stator 20 disposed adjacent one another.
- the turbine section 18 of the engine 10 may in fact include a plurality of axial turbines, thereby resulting in a plurality of turbine rotors 22 and turbine stators 20 in alternating sequence along the longitudinal axis 11 of the engine 10 .
- the static or non-rotating structures can include structures other that stators with airfoils.
- the non-rotating structures can include an inner wall of an interurban duct, for example in the case of a high pressure turbine stage, or the inner wall of an exhaust duct, for example in the case of the low pressure turbine stage 22 .
- rim seal 45 as described herein is not limited for use with turbine rotors and blades.
- the rim seal can also be used on either sides of a compressor rotor.
- the stator 20 has a plurality of vane airfoils 26 extending radially through the main gas path 24 outwardly from respective inner platforms 28 located at radially inner ends and outer shrouds (not shown) located at radially outer ends, and a plurality of vane mounting sections 30 extending radially inwardly from the respective inner vane platforms 28 .
- the vane mounting sections 30 are fastened to a central hub 32 of the stator 20 .
- a rotor 22 which in the case of a turbine rotor 22 within the turbine section 18 of the engine 10 is immediately upstream from the turbine stator 20 , has a plurality of rotor blades 34 extending radially outwardly from respective rotor platforms 36 which are mounted to the disk 40 of the rotor 22 by a plurality of blade roots 38 extending radially inwardly from the respective rotor platforms 36 .
- the blade roots 38 are configured to be received within corresponding slots formed within the disk 40 of the rotor 22 .
- the vane platforms 28 and the rotor platforms 36 are located at a radially inner end of the vane airfoils 26 and blades 34 .
- the rotor disk 40 defines a radial outer rim 41 axially extending between an upstream face 41 a and an opposed downstream face 41 b .
- the rotor disk defines an axial centerline 41 c located at a mid-plane between the rotor disk outer rim upstream and downstream faces 41 a and 41 b .
- An axial distance between the upstream 41 a and downstream 41 b faces defines a width W of the rotor disk outer rim 41 .
- the platforms 28 of the stator 20 are in abutment engagement with one another to define a circumferential stator flange 44 circumferentially extending around the axis 11 .
- the stator flange 44 extends axially away (e.g. upstream) toward the rotor 22 .
- the platforms 36 of the rotor 22 are in abutment engagement with one another to define a circumferential rotor flange 46 circumferentially extending around the axis 11 .
- the rotor flange 46 extends axially away (e.g. downstream) toward the stator 20 .
- the stator and rotor flanges 44 and 46 each define a continuous annular rim circumferentially extending around the axis 11 .
- the stator flange 44 rotates relative to the rotor flange 46 .
- a portion of the exhaust gases might leak from the annular gas path 24 in a radially inward direction represented by arrow 42 , between the rotor 22 and the downstream stator 20 .
- Such leaks might negatively impair performance because the turbine section 18 is unable to extract energy from the portion of the exhaust gases that leaks out of the annular main gas path 24 .
- a rim seal 45 arrangement is provided between the rotor 22 and the stator 20 . More particularly, the rim seal arrangement 45 is formed at least partially by the stator and rotor flanges 44 and 46 , which are radially offset from each other but which axially overlap each other by a predetermined axial distance to define an axial overlap 47 .
- the axial overlap 47 is defined by an axial distance 48 , parallel to the axis 11 between extremities, or remote ends, of the overlapping flanges 44 and 46 .
- the overlap 47 creates an air conduit C having a sinuous shape such as to offer a greater air resistance compared to a configuration without overlap.
- the exhaust gases flow in the annular gas path 24 in a direction represented by arrow F.
- the rotor 22 is upstream to the stator 20 relative to the flow direction F and the rotor flange 46 is radially outward relative to the stator flange 44 .
- the rotor annular rim defined by the rotor platforms 46 is radially offset by a radial gap distance 49 from the stator annular rim defined by the stator platforms 44 . Accordingly, an exhaust gas leak that enters in the air conduit C circulates in opposite direction relative to the exhaust gases direction F in a portion of the conduit C. However, it may be possible to dispose the stator flange 44 radially outward relative to the rotor flange 46 .
- heat in the turbine section 18 might cause thermal growth of the different parts of the turbine section 18 (e.g., stators/non-rotating or static structures 20 and rotors 22 ).
- the axial distance 48 of the overlap 47 might decrease when the engine 10 is in operation compared with the engine at rest.
- the “cold” overlap is greater than the “hot” overlap.
- the conduit C thus has a less sinuous, straighter shape. Hence, efficiency of the rim seal 45 may become reduced.
- the overlap 47 refers to the “cold” overlap unless otherwise indicated.
- the axial distances 50 between the stator flange 44 and the rotor platform 36 and between the rotor flange 46 and the stator vane airfoil 26 over the axial length L of the stator flange 44 are dictated by the tolerance stack up of all components of the turbine section 18 . Hence, increasing an axial length L of the flanges 44 and/or 46 might lead to friction between different parts of the stators 20 and of the rotors 22 .
- the rim seal arrangement 45 is modified by increasing the overlap 48 between the stator flange 44 and the rotor flange 46 while keeping the distances 50 substantially constant.
- the overlap 47 ′ is increased by increasing an axial length of the stator annular rim flange 44 .
- an annular trench 54 is formed in the rotor platform 36 at a location that is radially aligned with the stator platform annular rim 44 .
- the trench 54 is formed radially inwardly relative to the rotor flange 46 and radially outwardly relative to the rotor blade root 38 .
- the trench 54 is formed in a downstream surface 55 of the rotor 22 .
- the rotor trench 54 may be formed in one or more of the rotor blade platforms 36 , the blade roots 38 and/or the rotor disk 40 .
- the rotor trench 54 is provided in the form of an annular groove circumferentially extending around the axis 11 .
- An axial depth 53 of the rotor trench 54 relative to the axis 11 corresponds to the length increase 52 of the stator flange 44 .
- the trench axial depth 53 is defined between a base of the trench 54 a and an axially outer surface 36 a of the rotor platform 36 .
- the trench base 54 a is located axially further upstream than a downstream face 41 b of the rotor disk outer rim 41 .
- the depth 53 may be equal to or greater than the length increase 52 of the stator flange 44 .
- the base 54 a of the trench 54 is closer to the rotor disk axial centerline 41 c than are the rotor disk outer rim upstream and downstream faces 41 a and 41 b .
- the stator flange 44 is radially aligned relative to a radial length 56 of the rotor trench 54 to allow radial thermal displacement of the stator flange 44 relative to the rotor trench 54 .
- the stator flange 44 may be radially centered relative to the rotor trench 54 .
- the axial overlap distance 48 ′ is greater than the trench axial depth 53 .
- the axial overlap distance 48 ′ is greater than an axial distance 51 a between a remote end 44 a of the stator rim 44 and the axially outer surface 36 a of the rotor platform 36 .
- the axial overlap distance 48 ′ is greater than an axial distance 51 b between the stator rim remote end 44 a and a closest one of the upstream and downstream faces 41 a and 41 b of the rotor disk outer rim 41 .
- the axial overlap distance 48 ′ is greater than an axial distance 51 c between the stator rim remote end 44 a and the base of the trench 54 a.
- the rim seal arrangement is improved by providing a ratio of the axial overlap distance 48 ′ to the radial gap distance 49 equal to or greater than 1.
- the trench axial depth 53 is made less than the axial overlap distance 48 ′.
- an existing gas turbine engine 10 might be retrofit by forming the trench 54 in an existing rotor 22 .
- the forming of the trench 54 may be carried by a machining process.
- the trench 54 is formed until its base is located further closer to the mid-plane 41 c of the rotor disk outer rim 41 than are the upstream and downstream faces 41 a and 41 b of the rotor disk outer rim 41 .
- Others processes may be used without departing from the scope of the present disclose.
- the rotor 22 may be replaced by a new rotor already comprising the trench 54 .
- the rotor 22 comprises a plurality of blades 34 and respective blade roots 38 both radially extending from the platforms 36 .
- retrofitting the engine 10 comprises increasing the axial overlap distance 48 ′ such that it is greater than an axial distance between the stator flange remote end 44 a and at least one of the rotor platform axially outer surface 36 a , a closest one of the rotor disk outer rim upstream and downstream faces 41 a / 41 b , and the trench base 54 a .
- retrofitting the engine 10 comprises increasing the axial overlap distance 48 ′ such that a ratio of the overlap distance 48 ′ to the radial gap 49 is equal to or greater than 1.
- the length of the stator flange 44 is increased by adding material to the stator platform 28 using a process such as, but not limited to, brazing and soldering.
- the stator 20 may be replaced by a new stator having vanes with the elongated flanges 44 .
- the stator 20 comprises a plurality of vanes 26 and respective mounting sections 30 both radially extending from the platforms 28 .
- the stator flanges 44 of all the platforms 28 are elongated.
- the rim seal arrangement 45 is created by disposing the rotor disk 40 on the engine shaft 15 coincident with the axis 11 . Then, the stator hub 32 is also disposed on the engine shaft 15 until the stator platform 28 at least partially overlaps the rotor platform 36 an axial distance 48 .
- the axial distance 48 is increased to 48′ by moving the stator 20 such that the stator flange 44 is moved toward the rotor trench 54 until the axial distance 48 ′ is greater than an axial distance between the stator flange remote end 44 a and at least one of the rotor platform axially outer surface 36 a , a closest one of the rotor disk outer rim upstream and downstream faces 41 a / 41 b , and the trench based 54 a .
- the rim seal arrangement is created by having the axial overlap distance 48 ′ greater than the radial gap 49 such that a ratio of the overlap distance 48 ′ to the radial gap 49 is equal to or greater than 1.
- the new overlap 48 ′ is greater than the former overlap 48 by the length increase 52 .
- the present disclosure is not limited by the order of assembly described herein.
- the trench is not necessarily defined in the rotor 22 and may be defined in the stator 20 .
- both the rotor and the stator define trenches to accommodate the elongated flanges of the stator and the rotor.
- a trench has to be defined in a blade/airfoil vane of the rotor/stator.
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Abstract
Description
- The present application is a divisional of U.S. patent application Ser. No. 15/453,234 filed Mar. 8, 2017, the entire contents of which are incorporated herein by reference.
- The application relates generally to gas turbine engines and, more particularly, to a rim seal between a bladed rotor and an adjacent non-rotating structure in gas turbine engines.
- Compressors and turbines of a gas turbine engine generally have a plurality of stators and rotors in sequential disposition along a rotational axis. The rotating elements, such as compressor rotors and turbine rotors, operate at a very high rotation speed, and are mounted adjacent to and/or between non-rotating structures, such as stators, within the engine. These non-rotating structures are designed to be as close as possible to the rotating blade platforms, in order to mitigate pressurized gas ingestion inside the gas turbine engine. Typically, a rim seal arrangement is provided between the blade platforms of the rotor and the adjacent non-rotating structure in order to further limit losses from the main gas path.
- Various rim seal arrangements between the rotating elements, e.g. compressor rotors and turbine rotors, and their adjacent non-rotating structures, e.g. stator assemblies, have been used in the past. However, in some cases the axial space envelope of the engine is limited. The rotors may therefore not be axially positioned closer to their adjacent stators than a minimum threshold distance, due to clearance limitations imposed by the overall tolerance stack-up.
- Improved rim seal arrangements are therefore sought.
- There is accordingly provided a rim seal arrangement for a gas turbine engine comprising: a rotor having a rotor disk adapted to rotate about a longitudinal axis and a plurality of rotor blades circumferentially spaced apart about the rotor disk, the rotor disk defining an axial centerline plane at a midpoint between opposed upstream and downstream faces of the rotor disk at a radial outer rim of the rotor disk, each of the rotor blades including a rotor platform mounted to the rotor disk and an airfoil extending radially from the rotor platform to project within a main gas path of the gas turbine engine; a stator disposed adjacent to and axially spaced apart from the rotor, the stator including a plurality of vanes radially extending through the main gas path between a stator platform at a radially inner end and an outer shroud at a radially outer end; each of the rotor platforms including a rotor flange projecting axially toward the stator and abutting the rotor flange of a circumferentially adjacent rotor platform to form an annular rotor rim extending circumferentially around the longitudinal axis; each of the stator platforms having a stator flange projecting axially toward the rotor and abutting the stator flange of a circumferentially adjacent stator platform to form an annular stator rim extending circumferentially around the longitudinal axis, the annular stator rim being radially offset from the annular rotor rim by a radial gap distance, and the annular stator rim and the annular rotor rim axially overlapping each other by an axial overlap distance; and a trench defined in the rotor platform in radial alignment with the annular stator rim, the trench extending axially into the rotor platform to define an axial depth between a base of the trench and an axially outer surface of the rotor platform, the base of the trench being axially closer to the axial centerline plane of rotor disk than are the upstream and downstream faces of the rotor disk.
- There is also provided a rim seal arrangement for a gas turbine engine, comprising: a rotor including a set of rotating blades having blade platforms mounted to a rotor disk, a non-rotating structure disposed adjacent to and downstream of the rotor and axially spaced apart therefrom to define an annular space between the blade platforms and the adjacent non-rotating structure, and a rim seal formed between the non-rotating structure and the blade platforms of the rotor and extending through the annular space, the rim seal including an annular rotor rim extending downstream from the blade platforms towards the non-rotating structure and an annular static rim extending axially upstream from the non-rotating structure towards the rotor, the annular rotor rim being radially offset from the annular static rim by a radial gap distance, and the annular static rim and the annular rotor rim axially overlapping each other by an axial overlap distance, and a trench defined in the blade platforms adjacent to and in radial alignment with the annular static rim, the trench extending axially upstream into the blade platforms to define an axial depth, a base of the trench in the blade platforms being further upstream than a downstream face of the rotor disk at a radially outer rim thereof.
- There is further provided a method of forming a rim seal between a rotor and a stator in a turbine of a gas turbine engine, the stator being axially spaced apart from the rotor immediately downstream therefrom, the rotor including a set of turbine blades having blade platforms mounted to a rotor disk rotatable about a longitudinal axis, the method comprising: providing the rim seal between an annular rotor rim extending axially downstream from the blade platforms of the rotor and an annular stator rim extending axially upstream from the stator, the annular stator rim and the annular rotor rim axially overlapping each other by an axial overlap distance, and the annular stator rim and the annular rotor rim being radially offset by a radial gap distance; increasing the axial overlap distance by increasing an axial length of the annular stator rim; and forming a trench in the blade platforms of the rotor to accommodate the increased axial length of annular stator rim, the trench being radially aligned with the annular stator rim, the trench extending axially into the blade platforms to define an axial depth between a base of the trench and an axially outer surface of the blade platforms, the base of the trench being axially further upstream than a downstream face of the rotor disk at a radially outer rim thereof.
- There is further still provided a method of forming a rim seal between a rotor and a stator of a gas turbine engine, comprising: obtaining a rotor having a rotor disk rotatable about a longitudinal axis and having rotor blades protruding from rotor platforms, the rotor blades located radially outwardly of the rotor disk; obtaining a stator having vanes protruding from stator platforms; moving the rotor and the stator toward one another in an axial direction relative to the longitudinal axis until rotor flanges defined by the rotor platforms axially overlap stator flanges defined by the stator platforms; and further moving the rotor and stator toward one another in the axial direction to decrease an axial distance between ends of the stator platforms and bases of trenches defined by the rotor platforms, the bases of the trenches located axially closer to an axial centerline plane of the rotor disk than are upstream and downstream faces of the rotor disk.
- Reference is now made to the accompanying figures in which:
-
FIG. 1 is a schematic cross-sectional view of a gas turbine engine; -
FIG. 2a is a cross-sectional view of a portion of a turbine of the gas turbine engine ofFIG. 1 ; -
FIG. 2b is an enlarged view of a portion of the cross-sectional view ofFIG. 2 a; -
FIG. 3a is another cross-sectional view of a portion of a turbine of the gas turbine engine ofFIG. 1 ; -
FIG. 3b is an enlarged view of a portion of the cross-sectional view ofFIG. 3 a. - All figures are for illustration purposes only.
-
FIG. 1 illustrates agas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication afan 12 through which ambient air is propelled, acompressor section 14 for pressurizing the air, acombustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine section 18 for extracting energy from the combustion gases. Thefan 12, thecompressor 14, and theturbine section 18 are mounted on at least oneshaft 15. - Each of the
compressor section 14 and theturbine section 18 includes rotating elements, namely compressor rotors and turbine rotors, and static or non-rotating structures, including compressor stators and turbine stators. Arim seal 45, as will be described herein, is disposed between one or more of these rotors and an adjacent non-rotating structure, such as a stator. - Now referring to
FIG. 2a , in the illustrated embodiment, theturbine section 18 includes an axial turbine comprising aturbine rotor 22 and aturbine stator 20 disposed adjacent one another. Theturbine section 18 of theengine 10 may in fact include a plurality of axial turbines, thereby resulting in a plurality ofturbine rotors 22 andturbine stators 20 in alternating sequence along thelongitudinal axis 11 of theengine 10. Alternately, however, the static or non-rotating structures can include structures other that stators with airfoils. For example, the non-rotating structures can include an inner wall of an interurban duct, for example in the case of a high pressure turbine stage, or the inner wall of an exhaust duct, for example in the case of the lowpressure turbine stage 22. - It should be noted that the
rim seal 45 as described herein is not limited for use with turbine rotors and blades. The rim seal can also be used on either sides of a compressor rotor. - Still referring to
FIG. 2a , thestator 20 has a plurality ofvane airfoils 26 extending radially through themain gas path 24 outwardly from respectiveinner platforms 28 located at radially inner ends and outer shrouds (not shown) located at radially outer ends, and a plurality ofvane mounting sections 30 extending radially inwardly from the respectiveinner vane platforms 28. Thevane mounting sections 30 are fastened to acentral hub 32 of thestator 20. Arotor 22, which in the case of aturbine rotor 22 within theturbine section 18 of theengine 10 is immediately upstream from theturbine stator 20, has a plurality ofrotor blades 34 extending radially outwardly fromrespective rotor platforms 36 which are mounted to thedisk 40 of therotor 22 by a plurality ofblade roots 38 extending radially inwardly from therespective rotor platforms 36. Theblade roots 38 are configured to be received within corresponding slots formed within thedisk 40 of therotor 22. In the depicted embodiment, thevane platforms 28 and therotor platforms 36 are located at a radially inner end of thevane airfoils 26 andblades 34. - The
rotor disk 40 defines a radialouter rim 41 axially extending between anupstream face 41 a and an opposeddownstream face 41 b. The rotor disk defines anaxial centerline 41 c located at a mid-plane between the rotor disk outer rim upstream anddownstream faces outer rim 41. - In the embodiment shown, the
platforms 28 of thestator 20 are in abutment engagement with one another to define acircumferential stator flange 44 circumferentially extending around theaxis 11. Thestator flange 44 extends axially away (e.g. upstream) toward therotor 22. Similarly, theplatforms 36 of therotor 22 are in abutment engagement with one another to define acircumferential rotor flange 46 circumferentially extending around theaxis 11. Therotor flange 46 extends axially away (e.g. downstream) toward thestator 20. The stator androtor flanges axis 11. - Referring also to
FIG. 2b , thestator flange 44 rotates relative to therotor flange 46. During operation, a portion of the exhaust gases might leak from theannular gas path 24 in a radially inward direction represented byarrow 42, between therotor 22 and thedownstream stator 20. Such leaks might negatively impair performance because theturbine section 18 is unable to extract energy from the portion of the exhaust gases that leaks out of the annularmain gas path 24. - Still referring to
FIGS. 2a and 2b , arim seal 45 arrangement is provided between therotor 22 and thestator 20. More particularly, therim seal arrangement 45 is formed at least partially by the stator androtor flanges axial overlap 47. Theaxial overlap 47 is defined by anaxial distance 48, parallel to theaxis 11 between extremities, or remote ends, of the overlappingflanges overlap 47 creates an air conduit C having a sinuous shape such as to offer a greater air resistance compared to a configuration without overlap. In the illustrated embodiment, the exhaust gases flow in theannular gas path 24 in a direction represented by arrow F. In the embodiment shown, therotor 22 is upstream to thestator 20 relative to the flow direction F and therotor flange 46 is radially outward relative to thestator flange 44. The rotor annular rim defined by therotor platforms 46 is radially offset by aradial gap distance 49 from the stator annular rim defined by thestator platforms 44. Accordingly, an exhaust gas leak that enters in the air conduit C circulates in opposite direction relative to the exhaust gases direction F in a portion of the conduit C. However, it may be possible to dispose thestator flange 44 radially outward relative to therotor flange 46. - In a particular embodiment, heat in the
turbine section 18 might cause thermal growth of the different parts of the turbine section 18 (e.g., stators/non-rotating orstatic structures 20 and rotors 22). In some cases, theaxial distance 48 of theoverlap 47 might decrease when theengine 10 is in operation compared with the engine at rest. The “cold” overlap is greater than the “hot” overlap. In operating conditions, the conduit C thus has a less sinuous, straighter shape. Hence, efficiency of therim seal 45 may become reduced. For the remainder of this description, theoverlap 47 refers to the “cold” overlap unless otherwise indicated. - The
axial distances 50 between thestator flange 44 and therotor platform 36 and between therotor flange 46 and thestator vane airfoil 26 over the axial length L of thestator flange 44 are dictated by the tolerance stack up of all components of theturbine section 18. Hence, increasing an axial length L of theflanges 44 and/or 46 might lead to friction between different parts of thestators 20 and of therotors 22. - Now referring to
FIGS. 3a and 3b , therim seal arrangement 45 is modified by increasing theoverlap 48 between thestator flange 44 and therotor flange 46 while keeping thedistances 50 substantially constant. In a particular embodiment, theoverlap 47′ is increased by increasing an axial length of the statorannular rim flange 44. To accommodate alength increase 52 of thestator flange 44, anannular trench 54 is formed in therotor platform 36 at a location that is radially aligned with the stator platformannular rim 44. Thetrench 54 is formed radially inwardly relative to therotor flange 46 and radially outwardly relative to therotor blade root 38. In the illustrated embodiment, thetrench 54 is formed in adownstream surface 55 of therotor 22. Therotor trench 54 may be formed in one or more of therotor blade platforms 36, theblade roots 38 and/or therotor disk 40. - In the embodiment shown, the
rotor trench 54 is provided in the form of an annular groove circumferentially extending around theaxis 11. Anaxial depth 53 of therotor trench 54 relative to theaxis 11 corresponds to thelength increase 52 of thestator flange 44. The trenchaxial depth 53 is defined between a base of the trench 54 a and an axially outer surface 36 a of therotor platform 36. The trench base 54 a is located axially further upstream than adownstream face 41 b of the rotor diskouter rim 41. However, thedepth 53 may be equal to or greater than thelength increase 52 of thestator flange 44. The base 54 a of thetrench 54 is closer to the rotor diskaxial centerline 41 c than are the rotor disk outer rim upstream and downstream faces 41 a and 41 b. In a particular embodiment, thestator flange 44 is radially aligned relative to aradial length 56 of therotor trench 54 to allow radial thermal displacement of thestator flange 44 relative to therotor trench 54. Thestator flange 44 may be radially centered relative to therotor trench 54. - In the embodiment shown, the
axial overlap distance 48′ is greater than the trenchaxial depth 53. In a particular embodiment, theaxial overlap distance 48′ is greater than anaxial distance 51 a between aremote end 44 a of thestator rim 44 and the axially outer surface 36 a of therotor platform 36. In a particular embodiment, theaxial overlap distance 48′ is greater than anaxial distance 51 b between the stator rimremote end 44 a and a closest one of the upstream and downstream faces 41 a and 41 b of the rotor diskouter rim 41. In a particular embodiment, theaxial overlap distance 48′ is greater than anaxial distance 51 c between the stator rimremote end 44 a and the base of the trench 54 a. - In a particular embodiment, the rim seal arrangement is improved by providing a ratio of the
axial overlap distance 48′ to theradial gap distance 49 equal to or greater than 1. In a particular embodiment, to improve the rim seal arrangement, the trenchaxial depth 53 is made less than theaxial overlap distance 48′. - In a particular embodiment, an existing
gas turbine engine 10 might be retrofit by forming thetrench 54 in an existingrotor 22. The forming of thetrench 54 may be carried by a machining process. Thetrench 54 is formed until its base is located further closer to the mid-plane 41 c of the rotor diskouter rim 41 than are the upstream and downstream faces 41 a and 41 b of the rotor diskouter rim 41. Others processes may be used without departing from the scope of the present disclose. Alternatively, therotor 22 may be replaced by a new rotor already comprising thetrench 54. In the depicted embodiment, therotor 22 comprises a plurality ofblades 34 andrespective blade roots 38 both radially extending from theplatforms 36. Hence,trenches 54 are formed on all of therotor platforms 36 radially inwardly relative to therotor flanges 46 and radially outwardly relative to theblade roots 38 of therotor 22. In a particular embodiment, retrofitting theengine 10 comprises increasing theaxial overlap distance 48′ such that it is greater than an axial distance between the stator flangeremote end 44 a and at least one of the rotor platform axially outer surface 36 a, a closest one of the rotor disk outer rim upstream and downstream faces 41 a/41 b, and the trench base 54 a. In a particular embodiment, retrofitting theengine 10 comprises increasing theaxial overlap distance 48′ such that a ratio of theoverlap distance 48′ to theradial gap 49 is equal to or greater than 1. - In a particular embodiment, the length of the
stator flange 44 is increased by adding material to thestator platform 28 using a process such as, but not limited to, brazing and soldering. Alternatively, thestator 20 may be replaced by a new stator having vanes with theelongated flanges 44. In the depicted embodiment, thestator 20 comprises a plurality ofvanes 26 and respective mountingsections 30 both radially extending from theplatforms 28. Hence, thestator flanges 44 of all theplatforms 28 are elongated. - In a particular embodiment, the
rim seal arrangement 45 is created by disposing therotor disk 40 on theengine shaft 15 coincident with theaxis 11. Then, thestator hub 32 is also disposed on theengine shaft 15 until thestator platform 28 at least partially overlaps therotor platform 36 anaxial distance 48. Then, theaxial distance 48 is increased to 48′ by moving thestator 20 such that thestator flange 44 is moved toward therotor trench 54 until theaxial distance 48′ is greater than an axial distance between the stator flangeremote end 44 a and at least one of the rotor platform axially outer surface 36 a, a closest one of the rotor disk outer rim upstream and downstream faces 41 a/41 b, and the trench based 54 a. In a particular embodiment, the rim seal arrangement is created by having theaxial overlap distance 48′ greater than theradial gap 49 such that a ratio of theoverlap distance 48′ to theradial gap 49 is equal to or greater than 1. Thenew overlap 48′ is greater than theformer overlap 48 by thelength increase 52. The present disclosure is not limited by the order of assembly described herein. - Although the above description is directed to the
turbine 18 of agas turbine engine 10, it may be applicable to the gasturbine engine compressor 14. The trench is not necessarily defined in therotor 22 and may be defined in thestator 20. In another embodiment, both the rotor and the stator define trenches to accommodate the elongated flanges of the stator and the rotor. In this other embodiment, a trench has to be defined in a blade/airfoil vane of the rotor/stator. - The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
Claims (16)
Priority Applications (1)
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US16/825,031 US20200217214A1 (en) | 2017-03-08 | 2020-03-20 | Rim seal |
Applications Claiming Priority (2)
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US15/453,234 US10633992B2 (en) | 2017-03-08 | 2017-03-08 | Rim seal |
US16/825,031 US20200217214A1 (en) | 2017-03-08 | 2020-03-20 | Rim seal |
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US15/453,234 Division US10633992B2 (en) | 2017-03-08 | 2017-03-08 | Rim seal |
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US20200217214A1 true US20200217214A1 (en) | 2020-07-09 |
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US15/453,234 Active 2037-09-26 US10633992B2 (en) | 2017-03-08 | 2017-03-08 | Rim seal |
US16/825,031 Pending US20200217214A1 (en) | 2017-03-08 | 2020-03-20 | Rim seal |
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US15/453,234 Active 2037-09-26 US10633992B2 (en) | 2017-03-08 | 2017-03-08 | Rim seal |
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CA (1) | CA2992653A1 (en) |
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IT201900013218A1 (en) * | 2019-07-29 | 2021-01-29 | Ge Avio Srl | INTERNAL BAND FOR TURBINE ENGINE. |
US12055044B1 (en) | 2023-10-06 | 2024-08-06 | Pratt & Whitney Canada Corp. | Undercut groove and chamfer for rim seal |
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Also Published As
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CA2992653A1 (en) | 2018-09-08 |
US20180258781A1 (en) | 2018-09-13 |
US10633992B2 (en) | 2020-04-28 |
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