Patent Application
20210115855
The present disclosure relates to manifolds, and more particularly to fuel manifolds such as in gas turbine engines.
Gas turbine fuel manifolds have conventionally been located on the outside of the combustion case at the largest diameter of the engine surrounding the combustor.
The conventional techniques have been considered satisfactory for their intended purpose. However, there is an ever present need for improved systems and methods for manifolding, e.g. for fuel manifolds in gas turbine engines. This disclosure provides a solution for this need.
A system includes an internal manifold ring defining at least one circumferentially extending flow channel. A plurality of feed arms extend outward from the manifold ring.
A circumferentially segmented outer ring can be supported from the feed arms, outboard of the feed arms. Each feed arm can include a plurality of branches extending therefrom, wherein each branch is in fluid communication with the manifold ring through a respective one of the feed arms. A plurality of nozzles can be included, each nozzle connected to a respective one of the branches, wherein the system is devoid of nozzles radially inward from the manifold ring. The manifold ring can define a plurality of independent flow channels extending circumferentially therein. The feed arms can each define a plurality of independent flow channels therethrough, for individual staging of multipoint injection.
A main inlet can be included, extending radially inward to the manifold ring. The main inlet can extend along one of the feed arms. The main inlet can extend along an upstream side of one of the feed arms, e.g., wherein the branches described above extend to downstream facing nozzles. The main inlet can branch from the one of the feed arms in a y-junction proximate to the manifold ring. The main inlet can include a plurality of independent flow channels. The main inlet can extend inward from a position outward of an outer ring, e.g. the segmented outer ring as described above. An outer high pressure engine case can be included radially outside the outer ring, wherein the main inlet extends inward through the outer high pressure engine case. The high pressure engine case can be devoid of any additional inlets extending therethrough to the manifold ring. An inner high pressure engine case can be included radially inside the manifold ring. A combustor can be included wherein the manifold ring and feed arms are integrated in a combustor dome at an upstream end of the combustor.
A heat shield can extend about and shielding the one circumferentially extending flow channel. The system can be free of elastomeric seals. A method includes supplying fuel to a ring manifold of a gas turbine engine radially inward of all nozzles of the gas turbine engine.
These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings.
So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to certain figures, wherein:
Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an embodiment of a system in accordance with the disclosure is shown in
The system 100 includes an internal, inner manifold ring 102. A plurality of feed arms 104 extend outward from the manifold ring. An outer ring 106 is supported from the feed arms 104 and is radially outboard of the feed arms 104. The outer ring 106 can be circumferentially segmented, e.g., with one segment 108 suspended from each of the respective feed arms 104. Each feed arm can include a plurality of branches 110 extending therefrom, wherein each branch 110 is in fluid communication with the manifold ring 102 through the respective feed arms 104 from which the branch 110 extends. The branches 110 are omitted from the drawings for the most part for sake of clarity, however a few are shown in
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Due to the fact that traditional manifold rings are positioned radially outside of the combustor or even outside of the high pressure engine case, the system 100 provides a much smaller diameter for the manifold ring 102 than in traditional systems. This reduced diameter represents the potential for considerably lower weight. The reduction in diameter also provides reduced manifold volume, meaning system 100 allows very fast fill time relative to the traditional systems. No elastomeric seals are required by system 100 as they are required in traditional systems, hence the system 100 offers considerably reduced risk of overboard leaks. While providing the reduce weight as explained above, system 100 nonetheless still accommodates numerous flow channels and injection sites. The fuel can thus be supplied to a ring manifold of a gas turbine engine radially inward of all nozzles of the gas turbine engine.
The methods and systems of the present disclosure, as described above and shown in the drawings, provide for manifolding with superior properties including multipoint injection with a reduction of engine weight, fast fill time, and reduced risk of overboard leaks. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the scope of the subject disclosure.
