FR3125844B1 - Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement - Google Patents

Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement Download PDF

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Publication number
FR3125844B1
FR3125844B1 FR2108393A FR2108393A FR3125844B1 FR 3125844 B1 FR3125844 B1 FR 3125844B1 FR 2108393 A FR2108393 A FR 2108393A FR 2108393 A FR2108393 A FR 2108393A FR 3125844 B1 FR3125844 B1 FR 3125844B1
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FR
France
Prior art keywords
cone
flow
cooling flow
turbomachine
circulation
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.)
Active
Application number
FR2108393A
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English (en)
Other versions
FR3125844A1 (fr
Inventor
Adrien Pierre Jean Pertat
Paco Maurer
Nicolas Stoliaroff-Pepin
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2108393A priority Critical patent/FR3125844B1/fr
Priority to US18/293,904 priority patent/US12560104B2/en
Priority to EP22754132.3A priority patent/EP4381175A1/fr
Priority to PCT/FR2022/051465 priority patent/WO2023012419A1/fr
Priority to CN202280060952.5A priority patent/CN117940651A/zh
Publication of FR3125844A1 publication Critical patent/FR3125844A1/fr
Application granted granted Critical
Publication of FR3125844B1 publication Critical patent/FR3125844B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F01D25/305—Exhaust heads, chambers, or the like with fluid, e.g. liquid injection
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • 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
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne une turbomachine à double flux comportant un carter d’échappement (13) traversé par un flux primaire chaud (FP) et entouré par un flux secondaire froid (FS), et un cône (14) porté par ce carter d’échappement (13), ce carter d’échappement (13) comportant au moins un bras radial creux (18) traversant le flux primaire (FP) pour acheminer de l’air dans le cône (14) afin de former un flux de refroidissement (Ff’) de composants (26) situés dans ce cône (14), ce cône (14) comportant une paroi externe (21) et une paroi interne (22) qui longe la paroi externe (21) en étant radialement espacée de celle-ci pour délimiter un espace d’isolation thermique (EI) traversé d’amont en aval par le flux de refroidissement avant son évacuation par une ouverture de sortie (24) terminant le cône (14). Elle comporte un capot interne (29’) entourant au moins un composant (26) pour canaliser le flux de refroidissement (Ff’) afin qu’il longe ce composant pour le refroidir avant de traverser l’espace d’isolation thermique (EI) pour y être évacué. Figure pour l’abrégé : Figure 3
FR2108393A 2021-08-02 2021-08-02 Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement Active FR3125844B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2108393A FR3125844B1 (fr) 2021-08-02 2021-08-02 Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement
US18/293,904 US12560104B2 (en) 2021-08-02 2022-07-21 Turbomachine comprising an outlet cone incorporating components cooled by circulation of a cooling flow
EP22754132.3A EP4381175A1 (fr) 2021-08-02 2022-07-21 Turbomachine comportant un cone de sortie integrant des composants refroidis par circulation d'un flux de refroidissement
PCT/FR2022/051465 WO2023012419A1 (fr) 2021-08-02 2022-07-21 Turbomachine comportant un cone de sortie integrant des composants refroidis par circulation d'un flux de refroidissement
CN202280060952.5A CN117940651A (zh) 2021-08-02 2022-07-21 包括结合了通过冷却流的流通冷却的部件的出口锥体的涡轮机

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2108393 2021-08-02
FR2108393A FR3125844B1 (fr) 2021-08-02 2021-08-02 Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement

Publications (2)

Publication Number Publication Date
FR3125844A1 FR3125844A1 (fr) 2023-02-03
FR3125844B1 true FR3125844B1 (fr) 2024-01-12

Family

ID=77711188

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2108393A Active FR3125844B1 (fr) 2021-08-02 2021-08-02 Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement

Country Status (5)

Country Link
US (1) US12560104B2 (fr)
EP (1) EP4381175A1 (fr)
CN (1) CN117940651A (fr)
FR (1) FR3125844B1 (fr)
WO (1) WO2023012419A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3125844B1 (fr) * 2021-08-02 2024-01-12 Safran Aircraft Engines Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement
FR3150235A1 (fr) * 2023-06-23 2024-12-27 Safran Aircraft Engines Carter d’échappement cloisonné pour turbomachine
GB202312768D0 (en) * 2023-08-21 2023-10-04 Mclaren Automotive Ltd Improving acoustic efficiency
CN117386508A (zh) * 2023-09-12 2024-01-12 中国航发贵阳发动机设计研究所 一种带隔热层和气流冷却功能的内锥体结构
FR3154451B1 (fr) * 2023-10-20 2025-09-12 Safran Aircraft Engines Circuit de ventilation pour turbomachine
US12578092B2 (en) * 2024-01-12 2026-03-17 Rtx Corporation Cooled variable area nozzle for an aircraft engine
US12264623B1 (en) * 2024-01-18 2025-04-01 Honeywell International Inc. System for electric machine associated with gas turbine engine
FR3167174A1 (fr) * 2024-10-03 2026-04-10 Safran Aircraft Engines Turbomachine equipee d’une machine electrique et d’un dispositif de refroidissement
US20260235075A1 (en) * 2025-02-07 2026-08-13 Rtx Corporation Air system for aircraft propulsion system electric machine

Family Cites Families (17)

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Publication number Priority date Publication date Assignee Title
US1410726A (en) * 1919-08-18 1922-03-28 Jr James M Schoonmaker Apparatus for cooling internal-combustion engines
GB695482A (en) * 1950-11-28 1953-08-12 Rolls Royce Improvements in or relating to gas-turbine engines
US2932176A (en) * 1957-02-28 1960-04-12 United Aircraft Corp Cabin temperature control
GB0105349D0 (en) * 2001-03-03 2001-04-18 Rolls Royce Plc Gas turbine engine exhaust nozzle
CN100516469C (zh) * 2003-04-07 2009-07-22 阿尔斯通技术有限公司 涡轮机
US8099966B2 (en) * 2006-10-18 2012-01-24 Textron Innovations Inc. System and method for controlling an environment in an aircraft using a vortex cooler
US7578369B2 (en) * 2007-09-25 2009-08-25 Hamilton Sundstrand Corporation Mixed-flow exhaust silencer assembly
US20110239656A1 (en) * 2010-04-02 2011-10-06 Matthew Crume Water Augmentation System
US10094285B2 (en) * 2011-12-08 2018-10-09 Siemens Aktiengesellschaft Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
US20150138342A1 (en) * 2013-11-19 2015-05-21 United Technologies Corporation System and method to determine visible damage
US10801410B2 (en) * 2018-04-12 2020-10-13 Raytheon Technologies Corporation Thermal management of tail cone mounted generator
EP3581679B1 (fr) * 2018-06-01 2021-02-17 Rolls-Royce North American Technologies, Inc. Réparation de système de revêtement à base de suspension
FR3088955B1 (fr) * 2018-11-27 2020-12-25 Safran Aircraft Engines Turboréacteur à double flux comprenant un cône de sortie refroidi par son flux secondaire
US10975770B1 (en) * 2019-12-05 2021-04-13 Hamilton Sundstrand Corporation Integral engine case precooler
FR3125844B1 (fr) * 2021-08-02 2024-01-12 Safran Aircraft Engines Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement
EP4483042A1 (fr) * 2022-08-09 2025-01-01 Siemens Energy Global GmbH & Co. KG Moteur à turbine à gaz avec trajet d'écoulement de refroidissement de support d'aubage de turbine
US12286930B1 (en) * 2023-12-12 2025-04-29 Rolls-Royce North American Technologies Inc. Turbine engine fan case with bleed air for tip injection and heat exchanger cooling

Also Published As

Publication number Publication date
US12560104B2 (en) 2026-02-24
CN117940651A (zh) 2024-04-26
US20250122812A1 (en) 2025-04-17
FR3125844A1 (fr) 2023-02-03
EP4381175A1 (fr) 2024-06-12
WO2023012419A1 (fr) 2023-02-09

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