US3903691A - Method and devices for avoiding the formation of thermal imbalances in turbine engines - Google Patents

Method and devices for avoiding the formation of thermal imbalances in turbine engines Download PDF

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Publication number
US3903691A
US3903691A US342881A US34288173A US3903691A US 3903691 A US3903691 A US 3903691A US 342881 A US342881 A US 342881A US 34288173 A US34288173 A US 34288173A US 3903691 A US3903691 A US 3903691A
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Prior art keywords
engine
turbine
turbine wheel
stage
jet
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Expired - Lifetime
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US342881A
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English (en)
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Joseph Szydlowski
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • 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

Definitions

  • ABSTRACT Foreign Application Priority Data May 26, 1972 France A device for avoiding the formation of thermal imbalances affecting the rotating parts of turbine engines.
  • the device include passages and jets for injecting 68 11 /7 C w 1m 1. m (mm 9m 3 l- 0 m L C St on UH 55 [58] Field of Search........................ 60/3966, 39.19;
  • the degree of thermal imbalance depends on the time during which the turbine is stopped. While it occurs on all internal combustion engines utilizing a turbine, the magnitude of its consequences varies according to the engine structure. It is particularly marked in the case of engines which, in the course of being speeded up, cross a critical level of rotation speeds. During the passage of the engine through this critical speed a significant thermal imbalance can have serious consequences.
  • the engine must be rotated by means of an engine spinner for a certain time before start-up until the temperatures have become uniform.
  • the present invention has as its object the reduction of such downtimes by provision of simple and effective means and by a method of utilizing same, whereby the temperatures of the different parts of the rotating engine components are rendered uniform, as soon as the engine has stopped.
  • a gas turbine which according to the invention includes jets and passages connected to compressed air delivery pipes originating from a source external to the turbine engine.
  • the jets inject air at judiciously selected points inside the engine, preferably where the temperature is highest, thereby producing a swirling of the atmosphere surrounding the rotating components which are most liable to be affected by any thermal imbalance.
  • the invention further provides a method for utilizing such devices, in which the air injection is effected as soon as the engine stops, thus preventing the onset of thermal imbalances in the rotating engine components.
  • FIG. 1 is an axial half-sectional view of a gas turbine engine with an annular combustion chamber and central centrifugal fuel delivery, having air injection devices according to the invention
  • FIG. 2 shows on an enlarged scale that portion of the turbine engine in FIG. 1 in which the devices according to the invention are situated;
  • FIG. 3 is a partial cross-sectional view through III- III of FIG. 2.
  • FIG. I a gas turbine is shown having an annular combustion chamber formed between an outer wall 1 and an inner wall 2 and debouching into the turbine proper, generally depicted by the numeral 18, through a fixed inlet nozzle diaphragm 3 positioned up-stream of a first stage turbine wheel 4.
  • the inlet nozzle diaphragm comprises fixed hollow stator blades 5 which are restrained in slots formed in an outer ring 6 and an inner ring 7 and which are suitably welded to the rings.
  • the turbine 18 has three stages, the wheel 4 comprising the first stage, while the two other stages comprise turbine wheels 8 and 9. Between the consecutive wheels 4, 8 and 9 are interposed fixed nozzle diaphragms l0 and 11 of fixed stator blade construction.
  • the whole assembly is located within a turbine casing 12 which forms an envelope for the air flow delivered by a centrifugal compressor 13.
  • the entire volume of air from the compressor enters the combustion chamber through slits, openings and tubes with which both outer wall 1 and inner wall 2 are provided.
  • the air which enters the combustion chamber through inner wall 2 first passes through the hollow blades 5 of the first-stage nozzle diaphragm 3 and cools them in so doing.
  • nozzle diaphragm 3 and the first stage 4 of turbine 18 there is provided at least one air inlet 14 which feeds through a nozzle or jet 15 formed in the outer ring 6 of nozzle diaphragm 3.
  • jet l5 compressed air from an external source (not shown) is conveyed through a pipe 17 associated to air inlet 14 and is injected into the engine and causes air to swirl over the turbine and more particularly over the firststage wheel 4 thereof, which is its hottest part. This renders the temperatures of the different parts of the rotating components uniform.
  • the air injection is effected immediately after fuel combustion in the combustion chamber of the gas turbine ceases. This can be accomplished by providing suitable valving, automatic controls and the like.
  • the very formation of such imbalances is prevented by this method. This results in significant time saving and correspondingly shortened engine down-time, and also in a more efficient process of temperature equalization, since the high temperatures of the rotating components assist in the heat exchange with the injected air.
  • At least two jets must be provided in the envelope of nozzle diaphragm 3.
  • such jets are arranged evenly along the periphery of ring 6.
  • passages and jets are preferably directed obliquely rather than radially (FlG. 3), whereby the compressed air streams injected by them cause the air mass adjacent wheel 4 to be rotated about the turbine axis, thus assisting and accelerating the temperature equalization process.
  • the passages and jets 15 are preferably inclined in the normal direction of rotation of the turbine, but may be inclined in the opposite direction if desired.
  • the jets 15 may be disposed at other points in the turbine engine, an example being proximate the second and third stages of turbine 18, or ahead of the upstream end of the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US342881A 1972-05-26 1973-03-19 Method and devices for avoiding the formation of thermal imbalances in turbine engines Expired - Lifetime US3903691A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7218853A FR2185753B1 (de) 1972-05-26 1972-05-26

Publications (1)

Publication Number Publication Date
US3903691A true US3903691A (en) 1975-09-09

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Family Applications (1)

Application Number Title Priority Date Filing Date
US342881A Expired - Lifetime US3903691A (en) 1972-05-26 1973-03-19 Method and devices for avoiding the formation of thermal imbalances in turbine engines

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US (1) US3903691A (de)
FR (1) FR2185753B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214436A (en) * 1977-06-24 1980-07-29 Bbc Brown, Boveri & Co., Ltd. Thrust compensation and cooling system for gas turbines
US4249371A (en) * 1977-06-24 1981-02-10 Bbc Brown Boveri & Company Limited Method and apparatus for dissipating heat in gas turbines during shut-down
US4358926A (en) * 1978-09-05 1982-11-16 Teledyne Industries, Inc. Turbine engine with shroud cooling means
US6626637B2 (en) 2001-08-17 2003-09-30 Alstom (Switzerland) Ltd Cooling method for turbines
EP1630356A1 (de) * 2004-08-25 2006-03-01 Siemens Aktiengesellschaft Flüssigkeitseinspritzung in einer Gasturbine während einer Abkühlphase
US20060162338A1 (en) * 2005-01-21 2006-07-27 Pratt & Whitney Canada Corp. Evacuation of hot gases accumulated in an inactive gas turbine engine
ITFI20120046A1 (it) * 2012-03-08 2013-09-09 Nuovo Pignone Srl "device and method for gas turbine unlocking"
US20180223738A1 (en) * 2017-02-06 2018-08-09 United Technologies Corporation Starter air valve system with dual electromechanical controls

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2977915B1 (fr) 2011-07-12 2018-11-16 Safran Helicopter Engines Procede de demarrage d'une turbomachine reduisant le balourd thermique
US10502139B2 (en) 2015-01-28 2019-12-10 General Electric Company Method of starting a gas turbine engine including a cooling phase

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2468461A (en) * 1943-05-22 1949-04-26 Lockheed Aircraft Corp Nozzle ring construction for turbopower plants
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
US3286461A (en) * 1965-07-22 1966-11-22 Gen Motors Corp Turbine starter and cooling
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US3535873A (en) * 1967-10-24 1970-10-27 Joseph Szydlowski Gas turbine cooling devices
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2854296A (en) * 1954-05-20 1958-09-30 Maschf Augsburg Nuernberg Ag Gas turbine with automatic cooling means
US3451215A (en) * 1967-04-03 1969-06-24 Gen Electric Fluid impingement starting means

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2468461A (en) * 1943-05-22 1949-04-26 Lockheed Aircraft Corp Nozzle ring construction for turbopower plants
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
US3286461A (en) * 1965-07-22 1966-11-22 Gen Motors Corp Turbine starter and cooling
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US3535873A (en) * 1967-10-24 1970-10-27 Joseph Szydlowski Gas turbine cooling devices
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214436A (en) * 1977-06-24 1980-07-29 Bbc Brown, Boveri & Co., Ltd. Thrust compensation and cooling system for gas turbines
US4249371A (en) * 1977-06-24 1981-02-10 Bbc Brown Boveri & Company Limited Method and apparatus for dissipating heat in gas turbines during shut-down
US4358926A (en) * 1978-09-05 1982-11-16 Teledyne Industries, Inc. Turbine engine with shroud cooling means
US6626637B2 (en) 2001-08-17 2003-09-30 Alstom (Switzerland) Ltd Cooling method for turbines
US7752847B2 (en) 2004-08-25 2010-07-13 Siemens Akteingesellschaft Liquid injection in a gas turbine during a cooling down phase
WO2006021520A1 (de) * 2004-08-25 2006-03-02 Siemens Aktiengesellschaft Flüssigkeitseinspritzung in einer gasturbine während einer abkühlphase
US20070251210A1 (en) * 2004-08-25 2007-11-01 Hajrudin Ceric Liquid Injection in a Gas Turbine During a Cooling Down Phase
EP1630356A1 (de) * 2004-08-25 2006-03-01 Siemens Aktiengesellschaft Flüssigkeitseinspritzung in einer Gasturbine während einer Abkühlphase
US20060162338A1 (en) * 2005-01-21 2006-07-27 Pratt & Whitney Canada Corp. Evacuation of hot gases accumulated in an inactive gas turbine engine
ITFI20120046A1 (it) * 2012-03-08 2013-09-09 Nuovo Pignone Srl "device and method for gas turbine unlocking"
WO2013131968A1 (en) * 2012-03-08 2013-09-12 Nuovo Pignone Srl Device and method for gas turbine unlocking after shut down
CN104302874A (zh) * 2012-03-08 2015-01-21 诺沃皮尼奥内股份有限公司 用于在停机之后燃气涡轮机解锁的装置和方法
CN104302874B (zh) * 2012-03-08 2016-04-27 诺沃皮尼奥内股份有限公司 航改式涡轮机和用于在航改式涡轮机停机之后解锁的方法
RU2622356C2 (ru) * 2012-03-08 2017-06-14 Нуово Пиньоне СРЛ Устройство и способ разблокировки газовой турбины после ее остановки
US9845730B2 (en) 2012-03-08 2017-12-19 Nuovo Pignone Srl Device and method for gas turbine unlocking
US20180223738A1 (en) * 2017-02-06 2018-08-09 United Technologies Corporation Starter air valve system with dual electromechanical controls
US10669945B2 (en) * 2017-02-06 2020-06-02 Raytheon Technologies Corporation Starter air valve system with dual electromechanical controls

Also Published As

Publication number Publication date
FR2185753A1 (de) 1974-01-04
FR2185753B1 (de) 1976-06-11

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