EP2620596A2 - Système de diffusion de gaz d'échappement de turbine - Google Patents

Système de diffusion de gaz d'échappement de turbine Download PDF

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Publication number
EP2620596A2
EP2620596A2 EP13152397.9A EP13152397A EP2620596A2 EP 2620596 A2 EP2620596 A2 EP 2620596A2 EP 13152397 A EP13152397 A EP 13152397A EP 2620596 A2 EP2620596 A2 EP 2620596A2
Authority
EP
European Patent Office
Prior art keywords
exhaust diffuser
diffuser system
wall
turbine exhaust
manways
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.)
Withdrawn
Application number
EP13152397.9A
Other languages
German (de)
English (en)
Inventor
Deepesh Dinesh Nanda
Piotr Edward Kobek
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2620596A2 publication Critical patent/EP2620596A2/fr
Withdrawn legal-status Critical Current

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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
    • 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

Definitions

  • the subject matter disclosed herein relates to turbine exhaust diffuser systems and, more particularly, to manways in turbine exhaust diffuser systems.
  • a turbine system may include an exhaust diffuser system coupled to a turbine section downstream of the turbine section.
  • a turbine system may be either a gas turbine system or a steam turbine system.
  • a gas turbine system combusts a mixture of fuel and air to generate hot combustion gases, which in turn drive one or more turbines.
  • the hot combustion gases force turbine blades to rotate, thereby driving a shaft to cause rotation of one or more loads, e.g., electrical generators, and so forth.
  • the exhaust diffuser system receives the exhaust from the turbine. As the exhaust flows through diverging passages of the exhaust diffuser system, dynamic pressure of the exhaust flow may cause the static pressure in the exhaust diffuser system to increase.
  • Exhaust diffuser systems may contain manways that extend through the exhaust diffuser system radially from an outer wall to an inner hub, or wall, that surrounds an access tunnel.
  • the manways may contain pipes that provide lubrication oil and/or cooling air to the turbine system.
  • the pipes extend into the access tunnel of the exhaust diffuser system and may limit entry and/or use of the access tunnel, such as by blocking entry through an access door.
  • the arrangement of the manways may cause exhaust to flow around the manways and generate wakes. Undesirable vortex shedding may result from the wakes and may affect the structure of the exhaust diffuser system. Further, the vortex shedding may increase pressure loss of the exhaust diffuser system, increase noise of the exhaust diffuser system, and decrease the overall performance of the exhaust diffuser system.
  • a turbine exhaust diffuser system in a first aspect, includes an outer wall.
  • the turbine exhaust diffuser system also includes an inner wall formed by a converging inner passageway.
  • Turbine exhaust is configured to flow through an area between the outer wall and the inner wall.
  • the turbine exhaust diffuser system includes at least one manway extending from the outer wall to the inner wall. The at least one manway extends from the outer wall to the inner wall at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.
  • a turbine exhaust diffuser system in a second aspect, includes an outer wall of a turbine exhaust passageway.
  • the turbine exhaust diffuser system also includes an access passageway defined by an inner wall of the turbine exhaust passageway.
  • the access passageway is configured to enable an operator to enter the access passageway to perform maintenance on the turbine exhaust diffuser system.
  • the turbine exhaust diffuser system includes a plurality of manways extending from the outer wall of the turbine exhaust passageway to the access passageway. Each manway extends from the outer wall of the turbine exhaust passageway to the access passageway at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.
  • a turbine exhaust diffuser system in a third aspect, includes a plurality of manways extending between an outer wall and an interior access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.
  • certain embodiments of a turbine exhaust diffuser system include manways that extend through the exhaust diffuser system at an angle that is not perpendicular to a central axis of the exhaust diffuser system.
  • the manways may extend through the exhaust diffuser system at an angle that is shifted within the range of approximately 5 to 25 degrees, 3 to 15 degrees, or 10 to 30 degrees from being perpendicular to the central axis of the diffuser system (e.g., the angle between the manways and the central axis may be within a range of approximately 95 and 115 degrees, 93 to 105 degrees, or 100 to 120 degrees).
  • the manways may extend through the exhaust diffuser system at an angle that is shifted approximately 15 degrees from being perpendicular to the central axis of the diffuser system. Consequently, due to the manways not being perpendicular to the central axis of the exhaust diffuser system, the amount of space for operator entry into an access tunnel of the exhaust diffuser system is increased. Further, the amplitude and frequency of vortex shedding (i.e., the unsteady flow of exhaust around the manways) is decreased when compared to systems that have manways perpendicular to the central axis of the exhaust diffuser system. As such, the exhaust diffuser systems described herein not only facilitate maintenance of the exhaust diffuser systems by human operators, but also enhance operational characteristics of the exhaust diffuser systems.
  • the gas turbine engine 100 extends in an axial direction 102.
  • a radial direction 104 illustrates a direction extending outward from a central axis 105 of the gas turbine engine 100.
  • a circumferential direction 106 illustrates the rotational direction around the central axis 105 of the gas turbine engine 100.
  • the gas turbine engine 100 includes one or more fuel nozzles 108 located inside a combustor section 110.
  • the gas turbine engine 100 may include multiple combustors 120 disposed in an annular (e.g., circumferential 106) arrangement within the combustor section 110.
  • each combustor 120 may include multiple fuel nozzles 108 attached to or near a head end of each combustor 120 in an annular (e.g., circumferential 106) or other arrangement.
  • the compressed air from the compressor 124 is then directed into the combustor section 110, where the compressed air is mixed with fuel.
  • the mixture of compressed air and fuel is generally burned within the combustor section 110 to generate high-temperature, high-pressure combustion gases, which are used to generate torque within a turbine section 130 of the gas turbine engine 100.
  • multiple combustors 120 may be annularly (e.g., circumferentially 106) disposed within the combustor section 110 of the gas turbine engine 100.
  • Each combustor 120 includes a transition piece 172 that directs the hot combustion gases from the combustor 120 to the turbine section 130 of the gas turbine engine 100.
  • each transition piece 172 generally defines a hot gas path from the combustor 120 to a nozzle assembly of the turbine section 130, included within a first stage 174 of the turbine section 130 of the gas turbine engine 100.
  • the turbine section 130 includes three separate stages or sections 174 (i.e., first stage or section), 176 (i.e., second stage or section), and 178 (i.e., third stage or section, or last turbine bucket section). Although illustrated as including three stages 174, 176, 178, it will be understood that, in other embodiments, the turbine section 130 may include any number of stages.
  • Each stage 174, 176, and 178 includes blades 180 coupled to a rotor wheel 182 rotatably attached to a shaft 184.
  • each of the turbine blades 180 may be considered a turbine bucket, or a bucket.
  • Each stage 174, 176, and 178 also includes a nozzle assembly 186 disposed directly upstream of each set of blades 180.
  • the nozzle assemblies 186 direct the hot combustion gases toward the blades 180 where the hot combustion gases apply motive forces to the blades 180 to rotate the blades 180, thereby turning the shaft 184. As a result, the blades 180 and shaft 184 rotate in the circumferential direction 106.
  • the hot combustion gases flow through each of the stages 174, 176, and 178 applying motive forces to the blades 180 within each stage 174, 176, and 178.
  • the hot combustion gases may then exit the gas turbine section 130 into an exhaust diffuser system 188 of the gas turbine engine 100.
  • the exhaust diffuser system 188 reduces the velocity of fluid flow of the exhaust combustion gases from the gas turbine section 130, and also increases the static pressure of the exhaust combustion gases to increase the work produced by the gas turbine engine 100.
  • the last turbine bucket section 178 of the turbine section 130 includes a clearance 194 between ends of a plurality of last turbine bucket blades 195 (e.g., the last blade 180 of the gas turbine section 130) and a stationary shroud 196 disposed about the plurality of last turbine bucket blades 195.
  • an outer wall 198 of the exhaust diffuser system 188 extends from the stationary shroud 196.
  • a strut 200 is illustrated abutting the outer wall 198. Struts 200 are used to support the structure of the exhaust diffuser section 188.
  • a manway 202 extends between the outer wall 198 and an inner wall 204 of the exhaust diffuser system 188.
  • the manway 202 may encompass pipes or tubes that are used to transport fluids from outside the exhaust diffuser system 188 for use within the exhaust diffuser system 188.
  • the inner wall 204 is formed by the outside of an access tunnel or converging passageway 206.
  • the inner wall 204 may extend at an angle 205 that is not parallel to the central axis 105.
  • the angle 205 between the inner wall 204 and the central axis 105 may be approximately 5 to 10 degrees, 3 to 7 degrees, or 8 to 15 degrees.
  • the manway 202 extends through the exhaust diffuser system 188 at an angle that is not perpendicular to the central axis 105.
  • exhaust e.g., the exhaust combustion gases from the gas turbine section 130
  • the exhaust flow is directed around the manway 202 to exit the exhaust diffuser system 188.
  • the manway 202 may cause vortex shedding to occur.
  • the amplitude and frequency of the vortex shedding may be lower in the present embodiments than in systems with manways 202 that are perpendicular to the central axis 105.
  • FIG. 2 is a perspective view of an embodiment of the gas turbine exhaust diffuser system 188.
  • the struts 200 are disposed around the inner wall 204 of the exhaust diffuser system 188 and extend radially 104 from the inner wall 204 to the outer wall 198 of the exhaust diffuser system 188 and thereby structurally support the outer wall 198 of the exhaust diffuser system 188.
  • turbine exhaust flows into the exhaust diffuser system 188
  • the exhaust flows through an area between the inner wall 204 and the outer wall 198.
  • the exhaust flows around the struts 200, which alters the exhaust flow. Therefore, the properties of how the exhaust flows through the exhaust diffuser system 188 are affected by the shape and position of the struts 200.
  • FIG. 3 is a side view of an embodiment of the gas turbine exhaust diffuser system 188.
  • FIG. 3 illustrates how multiple struts 200 may be arranged around the inner wall 204 of the exhaust diffuser system 188.
  • the manways 202 are located behind the struts 200 (within the exhaust diffuser system 188).
  • the manways 202 also extend between the inner wall 204 and the outer wall 198 and may provide further support between the inner wall 204 and the outer wall 198.
  • three manways 202 are illustrated, however, other embodiments of the exhaust diffuser system 188 may have fewer or more manways 202.
  • FIG. 4 is a cross-sectional side view of an embodiment of the gas turbine exhaust diffuser system 188.
  • two manways 202 are depicted, a first manway 236 and a second manway 238.
  • the manways 202 extend from the outer wall 198 to the inner wall 204 and extend through an exhaust flow area 240 through which the turbine exhaust from the turbine section 130 flows.
  • the manways 202 are illustrated as having a generally race-track shaped wall, the manways 202 walls may have any suitable shape (e.g., cylindrical, airfoil, etc.). Further, the shape of the manways 202 may be designed to achieve optimal flow of exhaust around the manways 202.
  • pipes 241 and 242 may be disposed within the manways 202 and extend from the manways 202 into the access tunnel 206 defined within the inner wall 204 of the exhaust diffuser system 188.
  • the pipes 241 and 242 may be used for transporting fluid to be used by the turbine exhaust diffuser system 188.
  • the pipe 241 may be used to transport lubricating fluid (e.g., oil) through the manway 236 to the access tunnel 206 to be used by the exhaust diffuser system 188 (e.g., to lubricate bearings).
  • the pipe 242 may be used to transport cooling air or fluid through the manway 238 to the access tunnel 206 to be used for reducing the temperature of components within the exhaust diffuser system 188.
  • the pipes 241 and 242 extend through the access tunnel 206 from an entry location 243 (e.g., where the manways 202 intersect with the access tunnel 206) toward a strut region 244 of the access tunnel 206.
  • the access tunnel 206 forms a cone like shape which generally increases in diameter as the access tunnel 206 extends from the entry location 243 toward the strut region 244. Therefore, a distance 246 between the pipes 241 and 242 may be based on the entry location 243 of the pipes 241 and 242 into the access tunnel 206. As may be appreciated, the distance 246 between the pipes 241 and 242 may affect heat transfer that occurs between the pipes 241 and 242.
  • the distance 246 as well as the distances between the pipes 241 and 242 and the inner wall 204 may affect the ability of an operator to move through the access tunnel 206, such as to perform maintenance.
  • the manways 202 extend at an angle from the outer wall 198 toward the inner wall 204 that is not perpendicular to the central axis 105.
  • the location of the manways 202 may cause the pipes 241 and 242 to enter the access tunnel 206 at a location where the access tunnel 206 has a larger diameter than if the manways 202 extended toward the access tunnel 206 at an angle perpendicular to the central axis 105, assuming that the manways 202 extend from the same location of the outer wall 198 in both instances.
  • the distance 246 may increase and allow more space for an operator to move within the access tunnel 206. For example, the distance 246 may increase because the pipes 241 and 242 may extend from an entry location 243 where the access tunnel 206 has a larger diameter than in other entry locations.
  • the larger diameter enables the pipes 241 and 242 to remain a greater distance 246 from each other as they extend into the access tunnel 206, remain close to the inner wall 204, and extend toward the strut region 244.
  • heat transfer between the pipes 241 and 242 may decrease as the distance 246 increases.
  • An entry distance 248 is the distance between the pipes 241 and 242 and an access door 249 (at a downstream end of the access tunnel 206), which is used by an operator to enter the access tunnel 206. As may be appreciated, as the entry distance 248 increases, there is greater space for the operator to enter the access tunnel 206 through the access door 249.
  • the entry distance 248 is greater in the present embodiments than in systems where the manways 202 extend perpendicular to the central axis 105, again assuming that the manways 202 extend from the same location of the outer wall 198 in both instances.
  • each manway 202 There are generally two sides of each manway 202. Specifically, an upstream end 250 (e.g., the side of the manway 202 closest to the struts 200) and a downstream end 252 (e.g., the side of the manway 202 farthest from the struts 200). As illustrated, the angle between the manways 202 and the central axis 105 may be described using an upstream angle 254 (e.g., the angle between the upstream end 250 and the central axis 105) or a downstream angle 256 (e.g., the angle between the downstream end 252 of the manway 202 and the central axis 105).
  • an upstream angle 254 e.g., the angle between the upstream end 250 and the central axis 105
  • a downstream angle 256 e.g., the angle between the downstream end 252 of the manway 202 and the central axis 105.
  • the upstream angle 254 may be any suitable angle greater than 90 degrees (e.g., not perpendicular), and the downstream angle 256 may be any suitable angle less than 90 degrees (e.g., not perpendicular).
  • the upstream angle 254 may be within a range of approximately 95 to 115 degrees, 93 to 105 degrees, or 100 to 120 degrees.
  • the upstream angle 254 may be approximately 105 degrees.
  • the downstream angle 256 may be within a range of approximately 65 to 85 degrees, 75 to 87 degrees, or 60 to 80 degrees.
  • the downstream angle 256 may be approximately 85 degrees.
  • the upstream angle 254 and the downstream angle 256 are supplementary angles (i.e., they combine to equal 180 degrees).
  • exhaust flows through the exhaust diffuser system 188.
  • the exhaust enters the exhaust diffuser system 188, flows around the struts 200, then flows through the exhaust flow area 240 and around the manways 202 before the exhaust exits the exhaust diffuser system 188.
  • the manways 202 may cause vortex shedding to occur.
  • the amplitude and frequency of the vortex shedding may be lower than in systems with manways 202 that are perpendicular to the central axis 105. More specifically, because the manways 202 are angled away from the impinging flow of the exhaust, the amplitude and frequency of vortex shedding may be drastically reduced as compared to perpendicular manways 202.
  • the technical effects of the present invention include providing greater access for an operator to enter and maneuver within the access tunnel 206. Further, heat transfer between pipes within the access tunnel 206 is decreased as the pipes are moved away from each other within the access tunnel 206. In addition, the amplitude and frequency of the vortex shedding is decreased (e.g., the flow of exhaust through the exhaust diffuser system 188 is disturbed less). As a result, there may be a decrease in pressure loss, a decrease in noise, and an increase in overall diffuser performance in the present embodiments when compared to systems with manways 202 that are perpendicular to the central axis 105.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)
EP13152397.9A 2012-01-25 2013-01-23 Système de diffusion de gaz d'échappement de turbine Withdrawn EP2620596A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL397899A PL221113B1 (pl) 2012-01-25 2012-01-25 Układy dyfuzora wydechowego turbiny

Publications (1)

Publication Number Publication Date
EP2620596A2 true EP2620596A2 (fr) 2013-07-31

Family

ID=47631305

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13152397.9A Withdrawn EP2620596A2 (fr) 2012-01-25 2013-01-23 Système de diffusion de gaz d'échappement de turbine

Country Status (6)

Country Link
US (1) US20130189088A1 (fr)
EP (1) EP2620596A2 (fr)
JP (1) JP2013151934A (fr)
CN (1) CN103225520A (fr)
PL (1) PL221113B1 (fr)
RU (1) RU2013102779A (fr)

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Publication number Priority date Publication date Assignee Title
FR2997996B1 (fr) * 2012-11-12 2015-01-09 Snecma Support de tube d'evacuation d'air dans une turbomachine
FR2997997B1 (fr) * 2012-11-12 2014-12-26 Snecma Support de tube d'evacuation d'air dans une turbomachine
US10255406B2 (en) * 2015-02-24 2019-04-09 Siemens Corporation Designing the geometry of a gas turbine exhaust diffuser on the basis of fluid dynamics information
US10563543B2 (en) 2016-05-31 2020-02-18 General Electric Company Exhaust diffuser
US10612420B2 (en) * 2016-11-17 2020-04-07 General Electric Company Support structures for rotors
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

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GB846329A (en) * 1957-12-12 1960-08-31 Napier & Son Ltd Combustion turbine power units
CH672004A5 (fr) * 1986-09-26 1989-10-13 Bbc Brown Boveri & Cie
US5404713A (en) * 1993-10-04 1995-04-11 General Electric Company Spillage drag and infrared reducing flade engine
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US20080159856A1 (en) * 2006-12-29 2008-07-03 Thomas Ory Moniz Guide vane and method of fabricating the same
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Title
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Also Published As

Publication number Publication date
PL397899A1 (pl) 2013-08-05
JP2013151934A (ja) 2013-08-08
RU2013102779A (ru) 2014-07-27
CN103225520A (zh) 2013-07-31
US20130189088A1 (en) 2013-07-25
PL221113B1 (pl) 2016-02-29

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