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Combustor liner concentric support and method

A burner, lining technology, applied in the field of wear of combustion hardware, can solve the problem of inadmissibility (between the coating nozzle and the surface of the component, no coating, etc.

Inactive Publication Date: 2012-05-02
NUOVO PIGNONE SPA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Some part geometries where it is desired to coat, such as corners and various curves do not allow (between the coating nozzle and the part surface) to obtain the required inclination, which results in thin coatings or possibly no coating at all

Method used

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  • Combustor liner concentric support and method
  • Combustor liner concentric support and method
  • Combustor liner concentric support and method

Examples

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Embodiment Construction

[0023] The following detailed description of the exemplary embodiments refers to the accompanying drawings. The same reference numbers in different drawings identify the same or similar elements. Additionally, the drawings are not necessarily drawn to scale. Also, the following detailed description does not limit the invention. Instead, the scope of the invention is defined by the appended claims.

[0024] Reference throughout this specification to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the disclosed subject matter. Thus, appearances of the phrase "in one embodiment" or "in an embodiment" in various places throughout the specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.

[002...

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Abstract

Systems and methods provide for reducing motion which causes wear in a combustor. The method includes attaching a first end of a combustor liner (404) to a retainer (402) which encircles the first end of the combustor liner (404); attaching the retainer (402) to a combustor casing (406), wherein the retainer (402) acts as a spring between the combustor liner (404) and the combustor casing (406); reducing a relative motion between the combustor casing (406) and the combustor liner (404) along a longitudinal axis and a circumferential axis of the combustor liner (404) by the retainer (402); and locating the combustor liner (404) substantially concentrically within the combustor casing (406).

Description

technical field [0001] Embodiments of the subject matter disclosed herein relate generally to reducing wear, and more particularly to reducing wear on combustion hardware of gas turbine systems. Background technique [0002] Combustors are used in gas turbines to deliver hot combustion gases to the first stage of the turbine. Each combustor used in a gas turbine typically includes a fuel injection system having one or more fuel nozzles and a combustion chamber. A typical combustor may include a combustion liner, a transition piece connected to and extending between the combustor and the first stage of the turbine, and a flow sleeve. Passages are created between the combustion liner and the flow sleeve that allow at least a portion of compressor discharge air to be introduced into the combustion liner for mixing with fuel injected through the fuel nozzles and for cooling purposes. Additionally, the transition piece directs and conveys the hot combustion gases to the first s...

Claims

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Application Information

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IPC IPC(8): F23R3/60
CPCF23R3/60Y10T29/49229F02C7/00F23R3/42
Inventor G·H·加尼姆
Owner NUOVO PIGNONE SPA
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