RU2003101665A - HIGH PRESSURE TURBINE MOBILE BLADE, SUPPLY WITH EXIT EDGE WITH IMPROVED HEAT CHARACTERISTIC - Google Patents

HIGH PRESSURE TURBINE MOBILE BLADE, SUPPLY WITH EXIT EDGE WITH IMPROVED HEAT CHARACTERISTIC Download PDF

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Publication number
RU2003101665A
RU2003101665A RU2003101665/06A RU2003101665A RU2003101665A RU 2003101665 A RU2003101665 A RU 2003101665A RU 2003101665/06 A RU2003101665/06 A RU 2003101665/06A RU 2003101665 A RU2003101665 A RU 2003101665A RU 2003101665 A RU2003101665 A RU 2003101665A
Authority
RU
Russia
Prior art keywords
blade
high pressure
cavity
additional
pressure turbine
Prior art date
Application number
RU2003101665/06A
Other languages
Russian (ru)
Inventor
Жак БУРИ (FR)
Жак Бури
Морис ЖЮДЕ (FR)
Морис Жюде
Жаки ТАБАРДЕН (FR)
Жаки Табарден
Original Assignee
Снекма Моторс (Fr)
Снекма Моторс
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 Снекма Моторс (Fr), Снекма Моторс filed Critical Снекма Моторс (Fr)
Publication of RU2003101665A publication Critical patent/RU2003101665A/en

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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
    • F05D2240/81—Cooled platforms

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

1. Подвижная лопатка турбины высокого давления турбомашины, содержащая, по меньшей мере, один охлаждающий контур, который образован, по меньшей мере, одной полостью (24), проходящей радиально между вершиной (14В) и основанием (14А) пера лопатки (10), по меньшей мере, одним впускным отверстием для воздуха на одном радиальном конце полости или полостей для подачи охлаждающего воздуха в охлаждающий контур или контуры, и несколькими выпускными щелями (26), открытыми в полость или полости и выходящими на вогнутую сторону (16А) пера лопатки между основанием и вершиной лопатки по существу перпендикулярно продольной оси (Х-Х) лопатки, причем между щелью (28), ближайшей к основанию пера лопатки, и верхней поверхностью (22А) полки (22), которая образует внутреннюю стенку канала для потока газов сгорания через турбину высокого давления, предусмотрена соединительная зона (30), отличающаяся тем, что содержит дополнительную выпускную щель (32, 34) для охлаждающего воздуха, открытую в указанную полость и выходящую в указанную соединительную зону на участке, соответствующем продолжению выходной кромки (20).1. A movable blade of a high pressure turbine of a turbomachine, comprising at least one cooling circuit, which is formed by at least one cavity (24) extending radially between the top (14B) and the base (14A) of the blade blade (10), at least one air inlet at one radial end of the cavity or cavities for supplying cooling air to the cooling circuit or circuits, and several outlet slots (26) open into the cavity or cavities and facing the concave side (16A) of the blade feather between base and the top of the blade essentially perpendicular to the longitudinal axis (XX) of the blade, and between the slot (28) closest to the base of the blade feather and the upper surface (22A) of the shelf (22), which forms the inner wall of the channel for the flow of combustion gases through the turbine high pressure, there is a connecting zone (30), characterized in that it contains an additional outlet slot (32, 34) for cooling air, open in the specified cavity and emerging in the specified connecting zone in the area corresponding to the continuation of the output edge (20). 2. Лопатка по п.1, отличающаяся тем, что дополнительная щель имеет форму, выбранную из группы следующих форм: продолговатая, прямоугольная, треугольная или перевернутая Т-образная.2. The blade according to claim 1, characterized in that the additional gap has a shape selected from the group of the following forms: oblong, rectangular, triangular or inverted T-shaped. 3. Лопатка по п.2, отличающаяся тем, что указанная дополнительная щель имеет выпускное сечение, отличное от сечения ее канала подачи.3. The blade according to claim 2, characterized in that said additional slot has an outlet section different from that of its supply channel. 4. Лопатка по п.1, отличающаяся тем, что указанная дополнительная щель выполнена непосредственно при литье.4. The blade according to claim 1, characterized in that the specified additional gap is made directly during casting. 5. Лопатка по любому из пп.1-4, отличающаяся тем, что нижняя продольная поверхность (32А, 34А) дополнительной щели расположена непосредственно над указанной верхней поверхностью полки.5. The blade according to any one of claims 1 to 4, characterized in that the lower longitudinal surface (32A, 34A) of the additional slit is located directly above the indicated upper surface of the shelf. 6. Турбина высокого давления турбомашины, отличающаяся тем, что содержит множество подвижных лопаток (10), охарактеризованных в любом из предыдущих пунктов.6. High pressure turbine of a turbomachine, characterized in that it contains many movable blades (10), characterized in any of the previous paragraphs.
RU2003101665/06A 2002-01-23 2003-01-22 HIGH PRESSURE TURBINE MOBILE BLADE, SUPPLY WITH EXIT EDGE WITH IMPROVED HEAT CHARACTERISTIC RU2003101665A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0200802 2002-01-23
FR0200802A FR2835015B1 (en) 2002-01-23 2002-01-23 HIGH-PRESSURE TURBINE MOBILE TURBINE WITH IMPROVED THERMAL BEHAVIOR LEAKAGE EDGE

Publications (1)

Publication Number Publication Date
RU2003101665A true RU2003101665A (en) 2004-11-10

Family

ID=8871382

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003101665/06A RU2003101665A (en) 2002-01-23 2003-01-22 HIGH PRESSURE TURBINE MOBILE BLADE, SUPPLY WITH EXIT EDGE WITH IMPROVED HEAT CHARACTERISTIC

Country Status (7)

Country Link
US (1) US20030138322A1 (en)
EP (1) EP1333155A1 (en)
JP (1) JP2003214108A (en)
CN (1) CN1436919A (en)
CA (1) CA2418241A1 (en)
FR (1) FR2835015B1 (en)
RU (1) RU2003101665A (en)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE50306044D1 (en) * 2003-09-05 2007-02-01 Siemens Ag Shovel of a turbine
FR2864990B1 (en) * 2004-01-14 2008-02-22 Snecma Moteurs IMPROVEMENTS IN THE HIGH-PRESSURE TURBINE AIR COOLING AIR EXHAUST DUCTING SLOTS
US7097424B2 (en) * 2004-02-03 2006-08-29 United Technologies Corporation Micro-circuit platform
US7246999B2 (en) * 2004-10-06 2007-07-24 General Electric Company Stepped outlet turbine airfoil
FR2877034B1 (en) * 2004-10-27 2009-04-03 Snecma Moteurs Sa ROTOR BLADE OF A GAS TURBINE
GB2444483B (en) * 2006-12-09 2010-07-14 Rolls Royce Plc A core for use in a casting mould
CH699601A1 (en) * 2008-09-30 2010-03-31 Alstom Technology Ltd Blade for a gas turbine.
CN101767286B (en) * 2008-12-30 2013-06-05 沈阳黎明航空发动机(集团)有限责任公司 Finishing and machining locating process method of high- pressure turbine working blade
US8632297B2 (en) 2010-09-29 2014-01-21 General Electric Company Turbine airfoil and method for cooling a turbine airfoil
US8585350B1 (en) * 2011-01-13 2013-11-19 George Liang Turbine vane with trailing edge extension
JP2012189026A (en) * 2011-03-11 2012-10-04 Ihi Corp Turbine blade
US9045987B2 (en) * 2012-06-15 2015-06-02 United Technologies Corporation Cooling for a turbine airfoil trailing edge
US10107107B2 (en) 2012-06-28 2018-10-23 United Technologies Corporation Gas turbine engine component with discharge slot having oval geometry
EP2868867A1 (en) * 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Turbine blade
JP6245740B2 (en) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 Gas turbine blade
US20160090843A1 (en) * 2014-09-30 2016-03-31 General Electric Company Turbine components with stepped apertures
US10247009B2 (en) * 2016-05-24 2019-04-02 General Electric Company Cooling passage for gas turbine system rotor blade
FR3099523B1 (en) * 2019-08-01 2021-10-29 Safran Aircraft Engines Blade fitted with a cooling circuit
US20230151737A1 (en) * 2021-11-18 2023-05-18 Raytheon Technologies Corporation Airfoil with axial cooling slot having diverging ramp

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4601638A (en) * 1984-12-21 1986-07-22 United Technologies Corporation Airfoil trailing edge cooling arrangement
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
WO1998000627A1 (en) * 1996-06-28 1998-01-08 United Technologies Corporation Coolable airfoil for a gas turbine engine
JP3316418B2 (en) * 1997-06-12 2002-08-19 三菱重工業株式会社 Gas turbine cooling blade
US5975851A (en) * 1997-12-17 1999-11-02 United Technologies Corporation Turbine blade with trailing edge root section cooling
US6062817A (en) * 1998-11-06 2000-05-16 General Electric Company Apparatus and methods for cooling slot step elimination
CA2334071C (en) * 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade
US6609891B2 (en) * 2001-08-30 2003-08-26 General Electric Company Turbine airfoil for gas turbine engine

Also Published As

Publication number Publication date
US20030138322A1 (en) 2003-07-24
JP2003214108A (en) 2003-07-30
EP1333155A1 (en) 2003-08-06
FR2835015A1 (en) 2003-07-25
FR2835015B1 (en) 2005-02-18
CN1436919A (en) 2003-08-20
CA2418241A1 (en) 2003-07-23

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FA93 Acknowledgement of application withdrawn (no request for examination)

Effective date: 20060123