US3927521A - Multicone exhaust diffuser system for a gas turbine - Google Patents

Multicone exhaust diffuser system for a gas turbine Download PDF

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Publication number
US3927521A
US3927521A US433960A US43396074A US3927521A US 3927521 A US3927521 A US 3927521A US 433960 A US433960 A US 433960A US 43396074 A US43396074 A US 43396074A US 3927521 A US3927521 A US 3927521A
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United States
Prior art keywords
exhaust
gas turbine
motive fluid
hot motive
hot
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.)
Expired - Lifetime
Application number
US433960A
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English (en)
Inventor
Birger O Hugoson
Carl A Rohr
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Westinghouse Electric Corp
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Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US433960A priority Critical patent/US3927521A/en
Priority to CA214,015A priority patent/CA1008676A/en
Priority to JP14355774A priority patent/JPS5323445B2/ja
Application granted granted Critical
Publication of US3927521A publication Critical patent/US3927521A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D25/30—Exhaust heads, chambers, or the like

Definitions

  • This invention relates generally to gas turbines and more particularly to exhaust systems for gas turbines.
  • low pressure ends of axial flow elastic fluid turbines are usually provided with a diffuser for directing fluid discharged from the last stage turbine blades along a smooth aerodynamic path to the ambient atmosphere, as in the case of gas turbines.
  • Diffusers for large stationary gas turbines are often formed from radially spaced inner and outer fairing members forming an annularshaped exhaust outlet for the discharged fluid.
  • the downstream axis support bearing is disposed within the inner fairing member, and aerodynamically-shaped bearing support struts are disposed acrossthe hot exhaust gas annular flow path between the two fairing members.
  • the hearing support struts also, however, create a turbulent flow of exhaust gas, thereby reducing the efficiency of the diffuser in its ability to convert the kinetic energy of the moving fluid into pressure.
  • the discharged fluid does not move smoothly into the exhaust section of the turbine, with major consequences being a decrease in overall turbine efficiency.
  • the downstream support bearings, within the inner fairing member is disposed within an area that is difficult to reach and hence difficult to inspect without major dismantling of the exhaust system.
  • An object of the present invention is to overcome the problems presented above in the prior art.
  • Anotherobject of the present invention is to permit the shipping of as large a gas turbine as practically possible with minimum field assembly.
  • a still further object of the present invention is to provide an exhaust system for a gas turbine that will permit access to the downstream support bearing.
  • Yet another object of the present invention is to provide an exhaust system for a gas turbine having a minimum decrease in turbine efficiency due to the turbine exhaust gas diffuser.
  • a system for ducting hot exhaust gases from a gas turbine wherein the downstream bearing, shaft and last stage blades are accessible for service.
  • the exhaust gases after passing through the last stage blades, enter an annular chamber. From this chamber, the exhaust gases pass through transition members into conically-shaped ducts or diffusers which are in registration with the transition members and the annular chamber.
  • the conical diffusers have their in creasing diameters in the generally axially rearward direction.
  • Bearing support struts are disposed between the diffusers. This avoids the need for the support struts being disposed through the hot exhaust fluid flow area, which would decrease the overall turbine efficiency.
  • the arrangement also reduces the allowable transport or shipping size of the turbine, and reduce the downstream bearing, shaft and last stage blade accessibility.
  • FIG. 1 shows the exhaust end of a gas turbine with half of the exhaust system cut away
  • FIG. 2 is a side view of an exhaust diffuser arrangement showing the different zones therein;
  • FIG. 3 shows an arrangement of a pair of exhaust hoods that connect to the exit end of the diffuser cones.
  • FIG. 1 there is shown a portion of an axial flow gas turbine 10 including a rotatable shaft 12, a last stage rotor disc 14 mounted on said shaft 12, a plurality of radially directed blades 16 mounted on said disc 14, a bearing 18 supporting the downstream end of said shaft 12, a plurality of elongated bearing support struts 20, and an exhaust diffuser arrangement 22.
  • hot motive gas fluid is supplied through the motive fluid flow passageway, comprised of the rotating and stationary blades, only the rotating blades 16 of the last stage are shown. During flow past the blades, the hot motive gaseous fluid is expanded to impart rotational energy to the rotor.
  • the gas turbine 10 in the illustration shown is of the axial flow type, having a shell structure 24 and turbine support member 26.
  • the hot motive fluid is directed from the last row of blades 16 to an exhaust annulus 28, which is defined by a generally toroidal-shaped ring 30 on the downstream end of the gas turbine 10.
  • the toroidal-shaped ring 30 has a plurality of transition members 31 attached adjacent orifices, not shown, in the toroidal-shaped ring 30.
  • a plurality of diffuser cones 32 are attached to the transition members 31 and hence in registration with the toroidalshaped ring 30, which comprise the exhaust diffuser arrangement 22.
  • a dotted outline shown in FIG. 1 represents an exhaust hood member 37 which is part of the exhaust system.
  • Zone A is called the annular diffuser zone.
  • the walls of zone A are curved so as to act to suppress separation of the hot fluid exhaust gases.
  • a portion of the energy conversion from kinetic energy into static pressure can be made in the hot exhaust gases before entering the next zone, called the transition zone, and indicated by the letter B.
  • a slight reduction in cross-sectional area in the direction of the exhaust gas flow is introduced on the toroidal ring 30 adjacent the transition member 31, to keep the exhaust gas flow aligned.
  • the velocity distribution of the hot exhaust gas flow is kept as uniform as possible as it enters the third zone called the conical diffuser zone, and indicated by the letter C.
  • the transition member 31 and the exhaust diffuser cone 32 each have a flange, 33 and 34, at their juncture, to permit assembly thereby.
  • the exhaust hood arrangement 36 is shown in FIG. 3.
  • the exhaust hood arrangement 36 is comprised of at least two exhaust hood members 37 and 37
  • the exit ends of the conical diffuser cones 32 mate with orifices 38 in each exhaust hood member 37 and 37
  • the exhaust hoods 37 and 37 deflect and duct the hot fluid exhaust gases away from the turbine 10.
  • Tie bars 39 connect the exhaust hood members 37 and 37 to take the lateral forces generated therein by the turning of the hot gaseous exhaust fluid flow.
  • Axial forces within the exhaust hood members 37 and 37 are transmitted by other tie rods 41 back to the gas turbine support members 26.
  • Expansion joints 38 are provided at the junction of the diffuser cones 32 with the exhaust hood members 37 and 37.
  • the exhaust hood members 37 and 37' are each separate shippable members themselves, permitting simple field assembly.
  • the exhaust diffuser cones are easily removable for inspection and repair of the downstream bearing 18, the shaft 12 and the last stage blades 16.
  • the turbine itself may be shipped to the field without the exhaust diffuser arrangement 22 attached thereto.
  • Prior art arrangements require complete assembly before shipment because the bearing support struts extend through the exhaust annulus. That is, it must be assembled prior to shipment for support of the bearing and shaft. This reduces the maximum size of the turbine shippable because of the overall dimensional limitation imposed by the shipping envelope.
  • a gas turbine installation including: a housing, a shaft rotatably mounted in said housing by means including a downstream bearing, alternating annular arrays of stationary and rotatable blades, said rotatable blades being attached to said shaft, a hot motive fluid flow path within said housing, the hot motive fluids driving said rotatable blades, an inlet in said turbine for the hot motive fluid, and a hot motive fluid exhaust outlet arrangement for the hot motive fluid, said hot motive fluid exhaust outlet arrangement comprising:
  • said hot motive fluid exhaust ducts being detachable from said transition members, to permit access to the bearing and blade assemblies, said bearing support members being free from contact with the hot motive fluid exhaust to limit any thermal effects therein,
  • each of said exhaust hoods directing the flow of the hot motive fluid exhaust away from the gas turbine, each of said exhaust hoods having an array of half of said plurality of diffuser cones attached thereto.
  • downstream bearing is disposed axially beyond said annular chamber, said downstreambearing being generally in contact with the ambient air.
  • tie bars connect the two exhaust hoods together to restrain the lateral forces generated by the turning of the flow of exhaust gases.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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US433960A 1974-01-16 1974-01-16 Multicone exhaust diffuser system for a gas turbine Expired - Lifetime US3927521A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US433960A US3927521A (en) 1974-01-16 1974-01-16 Multicone exhaust diffuser system for a gas turbine
CA214,015A CA1008676A (en) 1974-01-16 1974-11-18 Multicone exhaust diffuser system for a gas turbine
JP14355774A JPS5323445B2 (cs) 1974-01-16 1974-12-16

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US433960A US3927521A (en) 1974-01-16 1974-01-16 Multicone exhaust diffuser system for a gas turbine

Publications (1)

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US3927521A true US3927521A (en) 1975-12-23

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US (1) US3927521A (cs)
JP (1) JPS5323445B2 (cs)
CA (1) CA1008676A (cs)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4874575A (en) * 1987-07-06 1989-10-17 Rockwell International Corporation Multiple discharge cylindrical pump collector
US20040240993A1 (en) * 2001-06-06 2004-12-02 Erling Jensen Air outlet unit for a large blower assembly
US20100037619A1 (en) * 2008-08-12 2010-02-18 Richard Charron Canted outlet for transition in a gas turbine engine
US20110236201A1 (en) * 2010-03-23 2011-09-29 Sumedhkumar Vyankatesh Shende Method and apparatus for radial exhaust gas turbine
CN109372637A (zh) * 2018-12-16 2019-02-22 中国航发沈阳发动机研究所 一种燃气轮机排气装置流路设计方法
CN109630219A (zh) * 2018-12-16 2019-04-16 中国航发沈阳发动机研究所 一种燃气轮机排气装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59156066U (ja) * 1983-04-07 1984-10-19 株式会社　京都紋付 難物とならない呉服用芯木
JP7566536B2 (ja) * 2020-08-28 2024-10-15 東芝エネルギーシステムズ株式会社 ガスタービンおよびガスタービンの製造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2655307A (en) * 1947-06-11 1953-10-13 Gen Electric Gas turbine rotor arrangement
US2922278A (en) * 1948-11-30 1960-01-26 Szydlowski Joseph Coaxial combustion products generator and turbine
US2933893A (en) * 1957-12-12 1960-04-26 Napier & Son Ltd Removable bearing support structure for a power turbine
US3448825A (en) * 1967-07-27 1969-06-10 Fred C Booth Process and apparatus for suppressing jet engine exhaust noise

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2655307A (en) * 1947-06-11 1953-10-13 Gen Electric Gas turbine rotor arrangement
US2922278A (en) * 1948-11-30 1960-01-26 Szydlowski Joseph Coaxial combustion products generator and turbine
US2933893A (en) * 1957-12-12 1960-04-26 Napier & Son Ltd Removable bearing support structure for a power turbine
US3448825A (en) * 1967-07-27 1969-06-10 Fred C Booth Process and apparatus for suppressing jet engine exhaust noise

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4874575A (en) * 1987-07-06 1989-10-17 Rockwell International Corporation Multiple discharge cylindrical pump collector
US20040240993A1 (en) * 2001-06-06 2004-12-02 Erling Jensen Air outlet unit for a large blower assembly
US7029234B2 (en) * 2001-06-06 2006-04-18 Howden Power A/S Air outlet unit for a large blower assembly
US20100037619A1 (en) * 2008-08-12 2010-02-18 Richard Charron Canted outlet for transition in a gas turbine engine
US8091365B2 (en) * 2008-08-12 2012-01-10 Siemens Energy, Inc. Canted outlet for transition in a gas turbine engine
US20110236201A1 (en) * 2010-03-23 2011-09-29 Sumedhkumar Vyankatesh Shende Method and apparatus for radial exhaust gas turbine
CN109372637A (zh) * 2018-12-16 2019-02-22 中国航发沈阳发动机研究所 一种燃气轮机排气装置流路设计方法
CN109630219A (zh) * 2018-12-16 2019-04-16 中国航发沈阳发动机研究所 一种燃气轮机排气装置
CN109630219B (zh) * 2018-12-16 2022-03-04 中国航发沈阳发动机研究所 一种燃气轮机排气装置

Also Published As

Publication number Publication date
JPS5323445B2 (cs) 1978-07-14
JPS50101712A (cs) 1975-08-12
CA1008676A (en) 1977-04-19

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