WO2017015747A1 - Système et procédé de refroidissement à plusieurs rayons - Google Patents

Système et procédé de refroidissement à plusieurs rayons Download PDF

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Publication number
WO2017015747A1
WO2017015747A1 PCT/CA2016/050825 CA2016050825W WO2017015747A1 WO 2017015747 A1 WO2017015747 A1 WO 2017015747A1 CA 2016050825 W CA2016050825 W CA 2016050825W WO 2017015747 A1 WO2017015747 A1 WO 2017015747A1
Authority
WO
WIPO (PCT)
Prior art keywords
tubular spokes
spokes
group
tubular
mid
Prior art date
Application number
PCT/CA2016/050825
Other languages
English (en)
Inventor
Guy Lefebvre
Remy Synnott
Original Assignee
Pratt & Whitney Canada Corp.
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 Pratt & Whitney Canada Corp. filed Critical Pratt & Whitney Canada Corp.
Priority to CN201680043556.6A priority Critical patent/CN107849938B/zh
Publication of WO2017015747A1 publication Critical patent/WO2017015747A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2300/00—Materials; Properties thereof

Definitions

  • the application relates generally to gas turbine engines and, more particularly, to a cooling arrangement for cooling the structural spokes of a mid-turbine frame module.
  • spokes it is known to use structural spokes to transfer loads from a bearing casing to an outer structural ring of a gas turbine engine.
  • spokes may be found in mid- turbine frame modules.
  • Each spoke typically extends radially from the outer ring through a strut in the gaspath to an inner ring supporting the bearing casing.
  • the spokes all around the module must be maintained at substantially the same temperature in order to prevent the bearing from becoming off-centered as a result of differential thermal growth between the spokes.
  • service lines are typically disposed in different struts than the one accommodating the spoke and cooled via dedicated cooling circuits to avoid potential contamination.
  • a mid-turbine frame module comprising an outer structural ring, an inner structural ring supporting a bearing, a plurality of circumferentially spaced-apart tubular spokes structurally interconnecting the inner structural ring to the outer structural ring, the spokes being connected in fluid flow communication with an air plenum and being used as air feed tubes.
  • a first portion of the spokes are used to direct purge air to a disc cavity of an adjacent turbine rotor.
  • the remaining spokes are used to feed/purge air and oil of a scupper line in the event of an oil seal failure.
  • a mid-turbine frame module comprising an outer structural ring, an inner structural ring supporting a bearing, a plurality of circumferentially spaced-apart tubular spokes structurally interconnecting the inner structural ring to the outer structural ring, first and second air cooling circuits connected in fluid flow communication with an annular plenum disposed radially outwardly relative to a gaspath, the first cooling circuit extending radially inwardly through a first portion of the spokes to a chamber located radially inwardly of the gaspath and wherein the second circuit extends from the annular plenum radially inwardly of the gas path through a second portion of the spokes.
  • a mid-turbine frame for a gas turbine engine, the mid-turbine frame comprising: an outer structural ring, an inner structural ring, an annular gas path between the inner and outer structural ring, a plurality of circumferentially spaced-apart hollow struts extending radially through the gas path, a plurality of circumferentially spaced-apart tubular spokes respectively extending internally through the hollow struts and structurally interconnecting the inner structural ring to the outer structural ring, the tubular spokes defining coolant flow passages extending generally radially across the gas path, the tubular spokes arranged and fluidly connected in first and second groups respectively forming parallel first and second cooling circuits, wherein the first cooling circuit is in fluid flow communication with a disc cavity of a turbine disc and the second cooling circuit is in fluid flow communication with an oil scupper line.
  • a mid-turbine frame module for a gas turbine engine, the module comprising: an outer structural ring, an inner structural ring, an annular gas path between the inner and outer structural ring, a plurality of circumferentially spaced-apart hollow struts extending radially through the gas path, a plurality of circumferentially spaced-apart tubular spokes extending internally through respective ones of the hollow struts for structurally interconnecting the inner structural ring to the outer structural ring, each of the tubular spokes defining a coolant flow passage extending radially through the gas path, the tubular spokes comprising first and second groups of tubular spokes respectively forming part of first and second separate cooling circuits, wherein the coolant flow passages of the first group of the tubular spokes are connected in fluid flow communication to a disc cavity of an adjacent turbine disc, and wherein the coolant flow passages of the second group of the tubular spokes are connected in fluid flow communication with
  • a spoke cooling arrangement for a gas turbine engine mid-turbine frame module comprising: a plurality of circumferentially spaced-apart tubular spokes structurally interconnecting an inner structural ring to an outer structural ring, the spoke cooling arrangement comprising: first and second separate cooling circuits connected to a common coolant source, the first cooling circuit including a first group of the tubular spokes arranged in parallel fluid flow relationship and fluidly linking the source of coolant to a disc cavity of an adjacent turbine disc, the second cooling circuit including a second group of the tubular spokes arranged in serial fluid flow relationship and fluidly linking the source of coolant to an oil scupper line.
  • FIG. 1 is a schematic cross-section view of a gas turbine engine
  • FIG. 2 is an isometric view of a mid-turbine frame module mounted in an engine outer case
  • Fig. 3 is an isometric view of the mid-turbine frame shown without the engine outer case
  • FIG. 4 is an enlarged view of a portion of the mid-turbine frame illustrating an air intake arrangement for uniformly distributing cooling air all around the module and avoid the formation of a local cold spot in the module;
  • FIG. 5 is a cross-section view of the air intake arrangement shown in Fig. 4;
  • Fig. 6a is a cross-section view of a portion of the mid-turbine frame module illustrating a cooling flow scheme through one of the spokes;
  • Fig. 6b is an enlarged view of a radially inner end portion of the spoke cooling flow scheme shown in Fig. 6a;
  • Fig. 6c is an enlarged view of a radially outer end portion of the spoke cooling flow scheme shown in Fig. 6a;
  • Fig. 7a is an end view of the mid-turbine frame module illustrating a first cooling circuit for structurally dedicated spokes, which do not accommodate any service lines, and a second cooling circuit for the top and bottom spokes, which integrate bearing housing service lines, the two circuits being separated to avoid air contamination;
  • Fig. 7b is an enlarged cross-section view of a radially inner outlet end portion of the first cooling circuit.
  • Fig. 7c is an enlarged cross-section view of a radially outer outlet end portion of the second cooling circuit.
  • Fig. 1 illustrates a turbofan 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 multistage compressor 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.
  • Figs. 2 and 3 show a portion of the turbine section 18. More particularly, Fig. 2 illustrates a mid-turbine frame module 20 housed within an engine outer case 21 . As shown in Fig. 3, the mid-turbine frame module 20 comprises an inner structural ring 22 adapted to receive and support a bearing casing 23, which is, in turn, adapted to support the main shafts of the engine 10. The bearing casing 23 may be detachably mounted to the inner ring 22 by means of bolts or the like.
  • the inner bearing support ring 22 is structurally supported by an outer structural ring 24 by means of a plurality of circumferentially distributed tubular spokes 26 (6 in the illustrated embodiment).
  • the spokes 26 centralize the inner ring 22 and, thus, the bearing casing 23 relative to the outer ring 24.
  • tubular spoke is herein intended to refer to generally refer to a hollow spoke structure and is, thus, not limited to any specific cross-sectional shape.
  • Each spoke 26 may extend radially through a hollow strut 29a, b (Fig. 6a) of a nonstructural integrated strut-vane (ISV) casing 28 "floatingly" mounted between the inner and outer structural rings 22 and 24 for guiding the combustion gases between two axially adjacent turbine stages.
  • the ISV casing 28 has a radially outer and a radially inner gaspath walls 28a, 28b (Figs. 5 and 6a) defining therebetween a portion of the gaspath of the turbine section 18.
  • the ISV casing 28 does not play a structural role. That is loads from the bearing casing 23 are not transmitted to the outer casing 24 via the ISV casing 28. The loads are rather transmitted through the spokes 26, which are shielded from the hot combustion gases by the hollow struts 29 of the ISV casing 28.
  • the spokes can be referred to as cold spokes.
  • a single external pipe may be used to direct coolant, such as bleed air from the compressor of the engine 10, to the mid-turbine frame module 20.
  • coolant such as bleed air from the compressor of the engine 10
  • a port 30 is provided on the engine outer case 21 for receiving cooling air from the external pipe. Cooling air from the engine outer case intake port 30 is then directed into an intake duct 32 mounted to the outer structural ring 24.
  • the intake duct 32 may be provided in the form of a generally T-shaped duct having an inlet branch 32a extending radially through a hole 34 defined in the outer ring 24 and a pair of outlet branches 32b extending laterally from opposed sides of the inlet branch 32a on a radially inner side of the outer ring 24.
  • the outlet branches 32b generally extend in circumferentially opposite directions and have respective outlet ends connected to outlet ports 36 provided on the outer ring 24 on opposed sides of the hole 34.
  • the intake duct 32 may be made in sheet metal, casting or any other suitable materials.
  • the outlet branches 32b of the air intake duct discharge the cooling air in circumferentially opposed directions into an annular cavity 40 defined between the engine outer case 21 and the outer ring 24.
  • the annular cavity 40 forms an air plenum all around the module.
  • the air plenum is in flow communication with the spokes and the hollow struts in which the spokes 26 are positioned.
  • cooling air may be uniformly distributed to the spokes 26 all around the cavity 40. It provides for an internal core passage architecture that distributes the cooling air in a circumferential manner to avoid unequal metal temperature in the mid- turbine frame module outer ring structure.
  • the air intake duct 32 prevents the incoming cooling air to be locally discharged directly against the outer ring 24, thereby avoiding the creation of a local cold spot thereon adjacent one of the spokes 26.
  • the air intake duct 32 rather splits the incoming flow of cooling air and redirects it with a radially outward and a circumferential component into the annular cavity 40 between the outer ring 24 and the engine outer case 21 .
  • the air impacts upon the engine outer case 21 and, thus, not on the outer ring 24, which is used to centralize the inner bearing casing 23 with the spokes 26. This contributes preserving the bearing centralization.
  • the above embodiment eliminates the use of multiple air cooling feed pipes, which may have a non-negligible impact on the overall weight of the engine. It also allows the introduction of cooling air in a restricted area. The air duct internal intake can also be easily replaced.
  • spokes are used to support and centralize the bearing casing 23.
  • Two of the spokes 26 are also used to accommodate bearing housing service lines 50, such as oil tubes.
  • Fig. 6a illustrates an example of a first hollow airfoil strut 29a containing a combined structural spoke 26a and bearing housing service line 50 and a second hollow airfoil strut 29b containing a structurally dedicated spoke 26b (spoke with no oil service lines).
  • the two structural spokes 26a with their internal bearing service lines 50 and the four structurally dedicated spokes 26b must be kept at substantially the same temperature to ensure rotor centralization. This may be achieved by providing in each of the 4 structurally dedicated spokes with an internal architecture that mimics the air circulation through the 2 spokes accommodating the bearing service lines 50.
  • a sleeve or tubular insert 52 may be provided in each of the 4 structurally dedicated spokes 26b to form an internal annular gap or annular reverse flow passage 54, which generally corresponds to the one between the combined spoke 26a and bearing housing service line 50 and associated surrounding strut 29a.
  • a first cooling circuit is formed between the annular cavity 40 and the 4 structurally dedicated spokes 26b. The coolant flows from the annular cavity 40 radially inwardly through the internal main coolant flow passage defined by the tubular insert 52 mounted inside each of the structurally dedicated spokes 26b. As shown in Fig.
  • the holes 56 are calibrated so that the portion of the cooling air flowing radially outwardly through the annular gap 54 maintains the spokes 26b substantially at the same temperature as the top and bottom spokes 26a housing the internal bearing service lines 50.
  • outlet holes 58 are defined in the radially outer end portion of the spokes 26b to discharge the cooling air between the ISV casing 28 and the outer ring 24.
  • This flow path mimics the cooling flow path around the top and bottom spokes 26a (Fig. 7a) used for the oil tubes/bearing service lines 50. This configuration ensures that all the structural spokes 26 with and without bearing housing service lines are kept at the same temperature, thereby ensuring bearing housing centralization throughout the engine operating envelope.
  • the cooling system comprises a second cooling circuit, which is separate from the first cooling circuit described above for the 4 structurally dedicated spokes 26b.
  • the second cooling circuit provides cooling to the top and bottom spokes 26a housing the service lines 50.
  • the annular gap between the bottom spoke 26a and the service line 50 extending therethrough is connected in fluid flow communication with the annular cavity or air plenum 40.
  • the air is discharged from the bottom spoke 26a into a sealed annular chamber or cavity 90 defined between the inner ring 22, the bearing casing 23 and a rear cover 92 (Fig. 7b) bolted to the inner ring 22.
  • the cooling air travels circumferentially through the annular cavity 90 from the bottom spoke 26a to the top spoke 26a. As shown in Fig 7a, the cooling air exits the annular cavity 90 via the annular gap defined between the top spoke 26a and the service line 50 extending therethrough. As shown in Fig. 7c, the air is discharged at a radially outer end of the service line 50 through outlet holes 94.
  • the person skilled in the art will appreciate that the top and bottom spokes 26a are used to feed/purge air and oil of a scupper line (schematically depicted by arrow 98 in Fig. 7c) in the case of oil failure.
  • the air in the first circuit through the 4 structurally dedicated spokes 26b will not be contaminated by the air flowing through the top and bottom spoke housing the service lines 50 in the event of oil leakage.
  • spokes 26b to feed secondary cooling air from the cavity 40 to the cavity disc of the upstream rotor also contributes to reduce the number of pipes and tubes. Indeed, the spokes are used as air feed tubes to direct cooling air to adjacent turbine components, thereby reducing the number of parts to be installed on the engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Un module de cadre intermédiaire de turbine comprend un anneau structural externe, un anneau structural interne et une pluralité de rayons espacés circonférentiellement, interconnectant structurellement l'anneau structural interne à l'anneau structural externe. Les rayons sont utilisés en tant que tuyau d'alimentation en air pour assurer le refroidissement de différents systèmes du moteur, tel qu'un conduit dalot d'huile et une cavité discale d'un disque de turbine adjacente.
PCT/CA2016/050825 2015-07-24 2016-07-13 Système et procédé de refroidissement à plusieurs rayons WO2017015747A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201680043556.6A CN107849938B (zh) 2015-07-24 2016-07-13 多辐条冷却系统及方法

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201562196500P 2015-07-24 2015-07-24
US201562196368P 2015-07-24 2015-07-24
US62/196,500 2015-07-24
US62/196,368 2015-07-24

Publications (1)

Publication Number Publication Date
WO2017015747A1 true WO2017015747A1 (fr) 2017-02-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CA2016/050825 WO2017015747A1 (fr) 2015-07-24 2016-07-13 Système et procédé de refroidissement à plusieurs rayons

Country Status (2)

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CN (1) CN107849938B (fr)
WO (1) WO2017015747A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10273812B2 (en) 2015-12-18 2019-04-30 Pratt & Whitney Canada Corp. Turbine rotor coolant supply system
CN111895259B (zh) * 2020-07-10 2021-11-12 中国航发湖南动力机械研究所 集成式储油箱

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120227371A1 (en) * 2011-03-09 2012-09-13 General Electric Company System for cooling and purging exhaust section of gas turbine engine
US20140205447A1 (en) * 2013-01-22 2014-07-24 Harry Patat Purge and cooling air for an exhaust section of a gas turbine assembly

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5118496B2 (ja) * 2008-01-10 2013-01-16 三菱重工業株式会社 ガスタービンの排気部の構造およびガスタービン

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120227371A1 (en) * 2011-03-09 2012-09-13 General Electric Company System for cooling and purging exhaust section of gas turbine engine
US20140205447A1 (en) * 2013-01-22 2014-07-24 Harry Patat Purge and cooling air for an exhaust section of a gas turbine assembly

Also Published As

Publication number Publication date
CN107849938B (zh) 2020-07-17
CN107849938A (zh) 2018-03-27

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