Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

Patent metadata

Field	Value
Publication number	US-10851997-B2
Application number	US-201715725751-A
Country	US
Kind code	B2
Filing date	Oct 5, 2017
Priority date	Oct 6, 2016
Publication date	Dec 1, 2020
Grant date	Dec 1, 2020

Abstract

A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first and said second tubular members.

First claim

The invention claimed is:

1. A combustor device for a gas turbines engine comprising:
a first tubular member and a second tubular member telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing means which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another;
the centering annular shoulder and an annular slot being arranged on a same end of the first tubular member, and wherein the sealing ring is arranged in the annular slot;
the centering annular shoulder protruding radially outwards from the first tubular member and stably slidingly abuts on a corresponding, complementary-shaped, annular mating portion of a radially inner surface of the second tubular member;
the sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first tubular member and the second tubular member; and
wherein the centering annular shoulder has a polygonal profile to prevent any relative axial rotation of the first tubular member and the second tubular member.

2. The combustor device according to claim 1 , wherein the annular slot is formed on the first tubular member axially spaced apart from the centering annular shoulder, so that the sealing ring and the centering annular shoulder stably abut against the radially inner surface of the second tubular member at respective annular mating portions spaced apart and separated relative to one another.

3. The combustor device according to claim 1 , comprising:
a first combustion chamber, wherein the first tubular member delimits the first combustion chamber which is configured for combustion of an inflammable mixture, and which is configured to internally accommodate a first burner adapted to mix fuel with compressed air for producing the inflammable mixture.

4. The combustor device according to claim 3 , wherein the second tubular member is telescopically fitted to the first tubular member for receiving hot gasses leaving the first combustion chamber, and comprising:
a series of pass-through holes and/or inwardly-protruding pipe fittings for allowing a dilution gas present outside, of the second tubular member to freely enter into the second tubular member for producing diluted hot gasses flowing inside the second tubular member.

5. The combustor device according to claim 4 , comprising:
a second combustion chamber, wherein the second tubular member is configured to internally accommodate a second burner adapted to mix the fuel to the diluted hot gasses flowing inside the second tubular member for producing a second inflammable mixture, and where the second tubular member at least partly delimits the second combustion chamber for combustion of the second inflammable mixture.

6. A gas turbine engine comprising:
a compressor for compression of air for producing a flow of compressed air;
a combustor assembly for combustion of a mixture of fuel and the compressed aft from the compressor for producing a flow of hot gasses;
an expansion turbine for expansion of the hot gasses from the combustor assembly; and
at least one of the combustor device according to claim 1 .

7. The gas turbine engine according to claim 6 , wherein the combustor assembly comprises:
a number of combustor devices of the at least one of the combustor device angularly staggered around an engine shaft of the gas turbine engine.

Assignees

• Ansaldo Energia Switzerland AG
• Ansaldo Energia Switzerlang Ag

Inventors

• Imfeld Jost
• Swiatek Slawomir
• Konradt Oliver

Classifications

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R3/42 Primary

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F23C6/047 Primary

  with fuel supply in stages · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title