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Integrated combustor nozzles with continuously curved liner segments

A burner and section technology, applied in the field of integrated burner nozzles, can solve problems such as difficult removal of integrated burner nozzles

Pending Publication Date: 2019-12-27
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Finally, the dogleg shape of the integrated burner nozzles and existing sealing efforts make it difficult to remove individual integrated burner nozzles

Method used

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  • Integrated combustor nozzles with continuously curved liner segments
  • Integrated combustor nozzles with continuously curved liner segments
  • Integrated combustor nozzles with continuously curved liner segments

Examples

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Embodiment Construction

[0067] Reference will now be made in detail to various embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar numerals in the drawings and description have been used to refer to like or like parts of the present disclosure.

[0068] To clearly describe the present integrated combustor nozzle, certain terminology will be used to refer to and describe relevant machine components within the scope of this disclosure. To the extent possible, common industry terminology will be used and adopted in a manner consistent with accepted term meanings. Unless otherwise specified, such terms should be given the broadest interpretation consistent with the context of this application and the scope of the appended claims. Those of ordinary skill in the art will recognize that several different or overlapping terms ma...

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Abstract

An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, anaft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.

Description

[0001] A Note About Government Funding [0002] The subject matter of this disclosure was made with support from the United States Government under Contract No. DE-FE0023965, awarded by the United States Department of Energy. The government has certain rights in this invention. technical field [0003] The present disclosure relates generally to the field of gas turbines, and more particularly, to integrated combustor nozzles that define separate combustion zones within an annular combustor and cause flow entering a turbine section to accelerate. The integrated combustor nozzle is provided with a continuously curved liner segment to facilitate installation and removal from the annular combustor. Background technique [0004] Some conventional turbines, such as gas turbine systems, are utilized to generate electricity. Typically, a gas turbine system includes a compressor, one or more combustors, and a turbine. Air can be drawn into the compressor via its inlet where it ...

Claims

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Application Information

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IPC IPC(8): F23R3/38
CPCF23R3/38F23R3/50F23R2900/00012F05D2250/713F05D2240/57F01D11/005F01D9/042F01D25/246F01D9/023F05D2220/3212F23R3/28F23R3/42F05D2240/35F23R3/002F01D9/04F05D2240/128F05D2240/55
Inventor J.D.贝里M.J.休斯R.P.德富里斯特K.W.麦马汉V.J.摩根I.塞泽尔N.N.萨拉瓦特D.特里维迪
Owner GENERAL ELECTRIC CO