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Pre-chamber Design Change to Eliminate High Pilot Tip Temperatures

IP.com Disclosure Number: IPCOM000201690D
Original Publication Date: 2010-Nov-18
Included in the Prior Art Database: 2010-Nov-18
Document File: 2 page(s) / 160K

Publishing Venue

Siemens

Related People

Juergen Carstens: CONTACT

Abstract

Current combustion systems of gas turbine engines often have issues of high pilot tip temperatures at medium to high load conditions. This is mainly caused due to the strong back flow of combustion products at high temperature which is formed due to the aerodynamic design of these combustion systems. The high pilot tip temperature may cause a problem for the fuel nozzles and can result in damage.

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This is the abbreviated version, containing approximately 52% of the total text.

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Pr -chamber Design Change

e to Eliminate High Pilot Tip Temperatures

Idea: Suresh Sadasivuni, Ph.D., GB-Lincoln

Current combustion systems of gas turbine engines often have issues of high pil medium to high load conditions. This is mainly caused due to the strong back flow of com products at high temperature which is formed due to the aerodynamic design of systems. The high pilot tip temperature may cause a problem for the fuel nozzle damage.

A nove
straight cylindrical pre-chamber design is changed to a converging-diverging portion creates a high velocity at the throat which will obstruct the back flow of high

also allows a uniform distribution of the reacting mixture

ot tip temperatures at bustion

these combustion s and can result in

l pre-chamber is designed in order to restrict the back flow of the combustion products. The . This design combusting products to

An advantage of the proposed pre-chamber design is the considerable reduced pilot tip temperature. It
in the main combustion zone as well.

Figure 1: combustion system with a known pre-chamber design

Swirler

pilot face.

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Pre-chamber

Main-Chamber


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© SIEMENS AG 2010 file: 2010J18898.doc page: 1


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Figure 2: known pre-chamber design compared with the proposed one

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