US3098355A - Starter nozzle for gas turbines - Google Patents

Starter nozzle for gas turbines Download PDF

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Publication number
US3098355A
US3098355A US72470A US7247060A US3098355A US 3098355 A US3098355 A US 3098355A US 72470 A US72470 A US 72470A US 7247060 A US7247060 A US 7247060A US 3098355 A US3098355 A US 3098355A
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US
United States
Prior art keywords
nozzle
casing
diaphragm
partitions
turbine
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
US72470A
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English (en)
Inventor
Varadi Louis Ernest
Bourque Theodore Edmond
Pesarek Walter
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
Priority to US72470A priority Critical patent/US3098355A/en
Priority to GB41438/61A priority patent/GB939882A/en
Priority to FR880114A priority patent/FR1307016A/fr
Priority to BE610872A priority patent/BE610872A/fr
Priority to DE1961G0033685 priority patent/DE1287860C2/de
Priority to CH1380061A priority patent/CH399835A/de
Application granted granted Critical
Publication of US3098355A publication Critical patent/US3098355A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/27—Fluid drives

Definitions

  • a fluid impingement starter nozzle for introducing a flow of starting fluid into a turbine requires that the fluid be conducted through the casing and into the working fluid flow path, and that it be directed to impinge at an appropriate angle upon the turbine buckets. It has been found expedient in the fulfillment of these requirements to extend nozzle-forming means at the desired angle through the casing and through the outer band of a nozzle diaphragm, for discharge between the partitions thereof. For example, it has been proposed to extend the contoured partitions of the nozzle diaphragm radially outwardly through the outer band, or alternatively to mount contoured stub vanes upon the interior of the casing to act as extensions of the partitions. The use of the partitions as guiding elements has been found desirable to provide a maximum effective nozzle length for optimum guidance of the starting fluid.
  • a starting nozzle box comprising a group of planar partition plates circumferentially spaced about a nozzle diaphragm.
  • An inner edge surface of each of the plates is secured to the outer edge of a corresponding nozzle partition, and the plate is inclined so that the edges defined by the parallel planar surfaces and the lower edge surface are parallel to lines tangent to trailing edge portions of the corresponding curved surface of the partition.
  • the leading and trailing edge surfaces of the partition plates lie in parallel planes, and are enclosed by cover plates to form a series of nozzle passages of parallelogram crosssection between the partition plates.
  • the partition plates extend outwardly from the nozzle diaphragm through an outer band thereof, and abut upon an interior surface of the casing.
  • the casing is formed with a plurality of circumferentially spaced ports arranged for alignment with the nozzle passageways, and a manifold extends arcuately about the casing to supply a flow of starting fluid through the nozzle box to the nozzle diaphragm and thence to the turbine.
  • the nozzle diaphragm is segmented for mounting in split halves of the casing. Means are provided for locating the diaphragm segments in predetermined positions in the casing halves, and these means serve to automatically align the starter nozzle passageways with the casing ports upon assembly of the engine.
  • the improved nozzle box affords 3,098,355 Patented July 23, 1963 sufficiently accurate direction of the starting fluid into the diaphragm for starting purposes, and comprises a substantially simplified and easily-constructed device.
  • FIG. 1 is an end view, partially in section, of a turbine engine incorporating a starter nozzle according to the invention
  • FIG. 2 is a fragmentary sectional end view showing the starter nozzle in relation to the engine casing and a nozzle diaphragm;
  • FIG. 3 is a sectional view taken along line 3-3 in FIG. 2, looking in the direction of the arrows;
  • FIG. 4 is a fragmentary plan view of the starter nozzle
  • FIG. 5 is a sectional view taken along line 55 in FIG. 3, looking in the direction of the arrows;
  • FIG. 6 is a fragmentary pictorial view illustrating retaining keys locating the nozzle diaphragm relative to the engine casing.
  • a turbine engine incorporating the improved starter nozzle includes a turbine wheel 10 rotatably mounted upon a shaft 11 and carrying a circumfcrentially spaced row of buckets 12 about the periphery thereof.
  • An annular casing 13 is circumferentially spaced about the turbine, and is provided with radial flanges 14 and 15 at its longitudinal extremities for attachment to adjoining casing sections of a turbine engine by means of suitable fasteners (not shown) received in a plurality of peripheral openings 16 and 17.
  • the casing is longitudinally split on a diametral plane at surfaces 18 to facilitate assembly of the turbine therein, and is formed with mating radial flanges 19 and 20 which are joined by suitable fasteners 21 to secure the assembly.
  • the casing is also provided with a plurality of internal circumferentially extending flanges, one of which is shown at 22, for the purpose of supporting at least one turbine shroud ring 23 in the casing.
  • the shroud ring is circumferentially spaced about the tips of the buckets 12 to prevent leakage of working fluid around them.
  • a turbine nozzle diaphragm generally designated 24 is provided for directing working fluid to the turbine buckets, and includes a circumferentially-spaced row of partitions 25.
  • the partitions extend radially between an inner composite mounting ring 26 and an outer composite mounting ring 27, which comprises an inner band 28 and an outer concentric band 29.
  • the partitions extend radially through the inner and outer bands 28 and 29, except that along a portion of the outer ring cooperating with the starting nozzle, the partitions are interrupted in edges 30 at the inner band.
  • the nozzle diaphragm is supported in a wellknown manner by the flange 22 and by an additional flange (not shown) spaced axially upstream in the casing.
  • a working fluid flow path 31 is thus defined by the nozzle diaphragm and the shroud ring 23.
  • a manifold 34 extends over an arcuate portion of the casing 13 and is brazed or otherwise secured thereto.
  • Starting fluid which may conveniently comprise air at a pressure of about 45 p.s.i., is introduced into an orifice 35 at a circumferential end of the manifold by any Wellknown means.
  • the casing is formed with a circumferentially-spaced series of ports 36 forming intermediate webs 37.
  • the openings 36 are in the form of parallelograms, as best shown in FIG. 4.
  • the provision of intermediate webs does not interfere with the air flow, and serves to maintain the rigidity of the casing in the region of the starting nozzle.
  • the openings divide the flow of starting fluid, as shown by the arrows in FIG. 1, into a plurality of streams for direction to individual partitions of the nozzle diaphragm.
  • the starting nozzle includes a nozzle box 40 which comprises a circumferentially-spaced series of planar partition plates 41 inclined circumferentially and laterally of the casing.
  • the plates are intersected by parallel leading and trailing edge surfaces 42 and 43, respectively, and by inner and outer edge surfaces 44 and 45, respectively.
  • Edges 46 and 47, defined by the edge surface 44 with the planar surfaces, respectively, of each partition plate, are disposed parallel to lines tangent to the contoured surfaces of the nozzle partitions in the vicinity of the trailing edges thereof.
  • the plates 41 pass through circumferentially extending openings 48 and 49 formed in the outer band 29 and the inner band 28, respectively, and are welded or brazed to the upper interrupted edges of corresponding nozzle partitions.
  • a series of passageways 50 are thus formed between adjacent plates 41, communicating the manifold 34 through the ports 36 with the working fluid flow path 31 between adjacent partitions.
  • the passageways 50 are enclosed by means of planar cover plates 51 and 52, which are brazed or welded to the upstream and downstream edges, respectively, of the plates 41, to enclose the passageways 5t) and to define their parallelogram cross-sectional form.
  • the plate 52 is formed with an arcuate flange 53 abutting the outer band 29 and brazed thereto to aid in securely supporting the nozzle box upon the diaphragm.
  • the nozzle diaphragm 24 is circumferentially segmented at the split surface 18 for mounting in the casing halves.
  • the segments are circumferentially slidable into the casing halves to a predetermined circumferential location in which their movement is stopped by a plurality of retaining keys 54, best shown by FIG. 6, which engage the circumferential end surfaces of the casing halves and the segments of the nozzle diaphragm at the split surfaces 18,
  • the retaining keys are more fully described in a copending application of Louis E. Varadi, Theodore E. Bourque, and Walter Pesarek, entitled Retaining Means for Turbine Shrouds and Nozzle Diaphragms of Turbine Engines, now Patent 3,056,083, issued October 2, 1962.
  • the specific means used for locating the nozzle diaphragm in a predetermined circumferential position are not critical to the present invention, and various wellknown means may be substituted for the retaining keys 54. Because the starting nozzle box is secured in a predetermined circumferential location upon the nozzle diaphragm, the alignment of the passageways 50 with the ports 36 of the casing automatically ensues upon the assembly of the elements of the engine.
  • planar surfaces of the partition plates of the nozzle box are not congruent with the curved surfaces of the trailing edges of the partitions, they provide a sufliciently close approximation to direct the starting fluid to the partitions in a satisfactory and effective manner.
  • the construction of the nozzle box of this invention provides advantages of simplicity and low manufacturing cost which offset its slight sacrifice of efficiency as compared with contoured starting nozzles.
  • a plurality of the nozzle boxes may be incorporated in a single nozzle diaphragm if desired.
  • a pair of diametrically opposed nozzle boxes may be utilized. A selected one of these may be actuated, to afford increased accessibility in varying nacelle installations; or both may be actuated to obtain additional starting torque.
  • a gas turbine engine comprising; an annular segmented casing enclosing a working fluid flow path, said casing formed with a row of circumferentially spaced ports therein, webs forming an integral part of said casing separating adjacent ones of said ports, a turbine mounted for rotation in said working fluid flow path, an annular segmented nozzle diaphragm including a row of circumferentially-spaced partitions having contoured surfaces and arranged to direct a stream of working fluid into said turbine, said diaphragm further including a segmented band circumferentially spaced about said partitions and secured to radially outer edges thereof, a starter nozzle box comprising a plurality of planar partition plates spaced apart circumferentially about said nozzle diaphragm interiorly of said casing, each of said plates extending inwardly through said band to the outer edge of a corresponding partition and secured thereto, each of said plates having edges adjacent to the corresponding partition disposed parallel to a tangent to a

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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)
US72470A 1960-11-29 1960-11-29 Starter nozzle for gas turbines Expired - Lifetime US3098355A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US72470A US3098355A (en) 1960-11-29 1960-11-29 Starter nozzle for gas turbines
GB41438/61A GB939882A (en) 1960-11-29 1961-11-20 Improvements in gas turbine engines incorporating nozzle starter
FR880114A FR1307016A (fr) 1960-11-29 1961-11-27 Tuyère de démarrage pour turbine à gaz
BE610872A BE610872A (fr) 1960-11-29 1961-11-28 Ajutage de démarreur pour turbines à gaz
DE1961G0033685 DE1287860C2 (de) 1960-11-29 1961-11-28 Gasturbinentriebwerk
CH1380061A CH399835A (de) 1960-11-29 1961-11-28 Anlassdüsengruppe für eine Gasturbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US72470A US3098355A (en) 1960-11-29 1960-11-29 Starter nozzle for gas turbines

Publications (1)

Publication Number Publication Date
US3098355A true US3098355A (en) 1963-07-23

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ID=22107806

Family Applications (1)

Application Number Title Priority Date Filing Date
US72470A Expired - Lifetime US3098355A (en) 1960-11-29 1960-11-29 Starter nozzle for gas turbines

Country Status (6)

Country Link
US (1) US3098355A (fr)
BE (1) BE610872A (fr)
CH (1) CH399835A (fr)
DE (1) DE1287860C2 (fr)
FR (1) FR1307016A (fr)
GB (1) GB939882A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3513326A (en) * 1967-05-22 1970-05-19 Harold S Potts Wind motor wheel

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB615689A (en) * 1946-07-16 1949-01-10 David Havelock Ballantyne Improvements in or relating to the starting of internal-combustion turbine plants
US2959919A (en) * 1958-01-02 1960-11-15 Gen Electric Gas impingement starter nozzle for turbines
US2971333A (en) * 1958-05-14 1961-02-14 Gen Electric Adjustable gas impingement turbine nozzles
US2989848A (en) * 1959-11-25 1961-06-27 Philip R Paiement Apparatus for air impingement starting of a turbojet engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB615689A (en) * 1946-07-16 1949-01-10 David Havelock Ballantyne Improvements in or relating to the starting of internal-combustion turbine plants
US2959919A (en) * 1958-01-02 1960-11-15 Gen Electric Gas impingement starter nozzle for turbines
US2971333A (en) * 1958-05-14 1961-02-14 Gen Electric Adjustable gas impingement turbine nozzles
US2989848A (en) * 1959-11-25 1961-06-27 Philip R Paiement Apparatus for air impingement starting of a turbojet engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3513326A (en) * 1967-05-22 1970-05-19 Harold S Potts Wind motor wheel

Also Published As

Publication number Publication date
FR1307016A (fr) 1962-10-19
DE1287860B (fr) 1969-01-23
CH399835A (de) 1965-09-30
BE610872A (fr) 1962-03-16
GB939882A (en) 1963-10-16
DE1287860C2 (de) 1969-09-18

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