US 11,852,344 B2
Tubular combustion chamber system and gas turbine unit having a tubular combustion chamber system of this type
Matthias Gralki, Mulheim an der Ruhr (DE); Claus Krusch, Essen (DE); and Daniel Schmidt, Mülheim an der Ruhr (DE)
Assigned to Siemens Aktiengesellschaft, Munich (DE)
Appl. No. 17/440,354
Filed by Siemens Aktiengesellschaft, Munich (DE)
PCT Filed Mar. 3, 2020, PCT No. PCT/EP2020/055501
§ 371(c)(1), (2) Date Sep. 17, 2021,
PCT Pub. No. WO2020/200609, PCT Pub. Date Oct. 8, 2020.
Claims priority of application No. 10 2019 204 544.8 (DE), filed on Apr. 1, 2019.
Prior Publication US 2022/0186928 A1, Jun. 16, 2022
Int. Cl. F23R 3/02 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/02 (2013.01) [F23R 3/007 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A tubular combustion chamber system for a gas turbine unit, comprising:
transition ducts which are arranged annularly about an axis and which are designed to be connected by their upstream ends in each case to a respective burner and to conduct hot gas produced by the burners to a turbine, and
a hot gas manifold which is designed for connection to the turbine and which defines an annular channel that is open to the turbine and into which downstream ends of the transition ducts open,
wherein radially inner and outer faces of the hot gas manifold that define the annular channel converge toward each other from an upstream end to a downstream end of the annular channel,
wherein the transition ducts and the hot gas manifold are made of metal and are provided internally with a refractory lining,
wherein a cross section of each transition duct tapers conically in a downstream direction,
wherein a refractory lining of each transition duct comprises at least one annular lining section whose outer diameter tapers conically in the downstream direction and which is held on the transition duct with radial and axial pretension,
wherein a refractory lining of the hot gas manifold comprises a multiplicity of manifold lining sections that are also prolongations of the downstream ends of the refractory linings of the transition ducts, and
wherein an inlet and an outlet of a select transition duct and a respective inlet of the hot gas manifold are all disposed at a common clocking position about the axis.