US20130081397A1

US20130081397A1 - Forward casing with a circumferential sloped surface and a combustor assembly including same

Info

Publication number: US20130081397A1
Application number: US13/252,525
Authority: US
Inventors: Brandon Taylor Overby
Original assignee: Individual
Current assignee: General Electric Co
Priority date: 2011-10-04
Filing date: 2011-10-04
Publication date: 2013-04-04
Also published as: CN103032901A; EP2578945A2

Abstract

A forward casing used in a combustor assembly for a turbine engine includes a circumferential sloped surface which reduces the total interior volume within the forward casing. The circumferential sloped surface can be flat or concave shaped.

Description

BACKGROUND

A combustor assembly for a turbine engine mixes compressed air with fuel, and the air-fuel mixture is then ignited to generate expanding combustion gases that drive the turbine. A partial cross-sectional view of a combustor assembly is illustrated in FIG. 1.
As shown in FIG. 1, the combustor assembly includes an aft casing 130 having a combustor liner 110 mounted therein. A flow sleeve 120 is also mounted inside the aft casing 130.
A forward casing 160 is attached to the forward end of the aft casing 130. An aft flange 167 on the forward casing 160 is used to attach the forward casing 160 to the aft casing 130. An end cover 170 is then attached to the forward end of the forward casing 160 via a forward flange 165.
A cap assembly 140 is mounted on the aft side of the forward casing 160. A plurality of cylindrical mounting elements 142 in the cap assembly 140 receive corresponding fuel nozzles 150 that deliver fuel into a flow of compressed air.
As illustrated by the arrows appearing in FIG. 1, compressed air is introduced into the combustor assembly through an annular space formed between the combustor liner 110 and the flow sleeve 120. This annular space extends past the end cap 140 and into an interior of the forward casing 160. As also illustrated by the arrows in FIG. 1, the compressed air introduced into the forward casing 160 then turns 180 degrees so that it can flow pass the fuel nozzles 150 where fuel is delivered into the flow of compressed air. The fuel-air mixture is then delivered into the interior 106 of the combustor liner 110, where it is ignited to create expanding gases which are used to drive the turbine.
As also illustrated in FIG. 1, a circumferential fuel supply passageway 162 is provided around the exterior of the forward casing 160. A plurality of radially extending fuel nozzles 164 extend inward from the inner wall of the forward casing 160. The fuel nozzles 164 are operatively coupled to the circumferential fuel passageway 162 so that the fuel in the circumferential fuel passageway 162 can be delivered into the compressed air flowing past the radially-extending fuel nozzles 164.
The geometry of the interior volume of the forward casing 160 can cause resonant vibrations to occur within the compressed air. The resonant vibrations, which are also referred to as “dynamics” are undesirable, and can harm the components of the combustor assembly, as well as lower the overall efficiency of the turbine engine. One way to reduce or eliminate resonant vibrations generated in the forward casing is to reduce the interior within the forward casing 160.
FIG. 2 illustrates another combustor assembly similar to the one described above in connection with FIG. 1. However, in the embodiment illustrated in FIG. 2 an insert 180 has been mounted inside the forward casing 160. A plurality of fasteners 183 are used to attach the insert 180 to the interior circumferential surface of the forward casing 160. The insert 180 includes a sloped or conical surface 182 which serves to reduce the interior volume within the forward casing. As noted above, this reduction in the interior volume of the forward casing 160 can help to reduce or eliminate undesirable resonant vibrations.
Because the insert 180 is attached to the forward casing 160 with fasteners 183, there is a possibility that one or more of the fasteners 183 may loosen or break off during operation of the turbine engine. If this were to occur, there is a possibility that a fastener 183 would be swept through the combustor liner 110 and into the turbine section of the turbine engine. Once in the turbine section, the fastener 183 would impact the rotating turbine blades and the stationary stator blades, which is likely to cause extensive damage to the turbine engine, requiring immediate shutdown and repair.
While there may only be a small likelihood that one of the fasteners 183 used to attach the insert 180 to the forward casing 160 might come loose, the amount of damage which could occur if this happens is extensive and very expensive. It would also result in the shutdown of a turbine engine, which could severely impact a power plant's ability to produce sufficient electrical power.

SUMMARY OF THE INVENTION Brief Description of the Drawings

FIG. 1 is a cross-sectional view of a portion of a combustor assembly of a turbine engine;

FIG. 2 is a cross-sectional view of a portion of a combustor assembly of a turbine engine which includes a removable insert mounted in the forward casing;

FIG. 3 is a partial perspective view of an integral forward casing which includes a sloped-circumferential surface;

FIG. 4 is partial cross-sectional view of a combustor assembly of a turbine engine which includes the integral forward casing illustrated in FIG. 3; and

FIG. 5 is a partial cross-sectional view of a portion of a combustor assembly of a turbine engine which includes an integral forward casing as illustrated in FIG. 3 with a concave circumferential sloped surface.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

For all the reasons explained above in the Background Section, attaching a removable insert to the interior of a forward casing of a combustor assembly is potentially dangerous, in that the fasteners used for this purpose can come loose and be sucked into the turbine section of the turbine engine. For these reasons, the benefits obtained through the use of an insert may be outweighed by the potential damage that can occur.
FIG. 3 illustrates a new forward casing for a combustor assembly of a turbine engine. The forward casing 300 includes a generally-cylindrical body with an aft mounting flange 367 formed at a first end of the cylindrical body. The aft mounting flange 367 is used to attach the forward casing 300 to an aft casing of a combustor assembly. In addition, a forward mounting flange 365 located on a second end of the generally-cylindrical body is used to attach the forward casing 300 to an end cover of a combustor assembly. The forward casing 300 also includes a circumferential fuel passageway 362 which feeds fuel to a plurality of inward, radially-extending fuel nozzles 364.
The forward casing illustrated in FIG. 3 also includes a circumferential sloped surface 368 which slopes inward towards the forward side of the cylindrical body. A radially-extending end portion 366 then extends from the smallest diameter portion of the circumferential sloped surface 368 back to the forward mounting flange 365.
A forward casing having a circumferential sloped surface as illustrated in FIG. 3 provides the benefits of the removable insert 180 illustrated in FIG. 2. Specifically, the circumferential sloped surface 368 reduces the total interior volume of the forward casing to help reduce or eliminate undesirable resonant vibrations which can otherwise occur. However, because the circumferential sloped surface 368 is an integral part of the forward casing 300, there's no possibility of a fastener coming loose and causing damage to the turbine engine.
FIG. 4 shows a partial cross-sectional view of a portion of a combustor assembly having an integral forward casing as illustrated in FIG. 3. As shown by the arrows in FIG. 4, compressed air entering the forward casing will be deflected by the circumferential sloped surface 368 of the integral forward casing 300 to help turn the flow of compressed air so that it can reverse direction. In addition, as illustrated in FIG. 4, the circumferential sloped surface 368 serves to reduce the interior volume within the forward casing.
FIG. 5 shows another cross-sectional view of a portion of a combustor assembly which includes an integral forward casing with a circumferential sloped surface 568. In this embodiment, the circumferential sloped surface 568 has a concave shape. The concave shape of the circumferential sloped surface 568 may better assist in turning the flow of compressed air so that it can reverse direction within the forward casing.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

What is claimed is:

1. A combustor assembly for a turbine engine, comprising:

an end cover;

an aft casing having a combustor liner mounted therein;

a cap assembly mounted between the forward casing and the end cover;

at least one fuel nozzle mounted on the cap assembly; and

an integral forward casing mounted between the aft casing and the end cover, wherein the forward casing includes a circumferential sloped surface that that slopes inward from the aft casing side to the end cover side of the forward casing.

2. The combustor assembly of claim 1, wherein the integral forward casing includes a circumferential fuel passageway that extends around an outer side of the forward casing.

3. The combustor assembly of claim 2, further comprising a plurality of fuel nozzles that extend radially inward from an inner wall of the forward casing, and that are operatively coupled to the circumferential fuel passageway such that fuel in the circumferential fuel passageway is fed into the plurality of fuel nozzles.

4. The combustor assembly of claim 3, wherein the circumferential sloped surface of the integral forward casing is located on the end cover side of the plurality of fuel nozzles.

5. The combustor assembly of claim 1, wherein the circumferential sloped surface is flat, such that the circumferential sloped surface is conical.

6. The combustor assembly of claim 1, wherein the circumferential sloped surface is concave shaped.

7. The combustor assembly of claim 1, wherein the integral forwarding casing includes a generally cylindrical body, and wherein the generally cylindrical body and the circumferential sloped surface are formed as a single integral part.

8. An integral forward casing for a combustor assembly of a turbine engine, comprising:

a generally cylindrical body;

an aft mounting flange located at a first end of the generally cylindrical body and that is configured to be attached to an aft casing of a combustor assembly;

a forward mounting flange located at a second end of the generally cylindrical body and that is configured to be attached to an end cover of a combustor assembly; and

a circumferential sloped surface that is integrally formed on an inner side of the generally cylindrical body, wherein a diameter of an end of the circumferential sloped surface located closest to the second end of the generally cylindrical body is smaller than a diameter of an end of the circumferential sloped surface located closest to the first end of the generally cylindrical body.

9. The integral forward casing of claim 8, wherein the integral forward casing includes a circumferential fuel passageway that extends around an outer side of the generally cylindrical body.

10. The integral forward casing of claim 9, further comprising a plurality of fuel nozzles that extend radially inward from an inner wall of the generally cylindrical body and that are operatively coupled to the circumferential fuel passageway such that fuel in the circumferential fuel passageway is fed into the plurality of fuel nozzles.

11. The integral forward casing of claim 10, wherein the circumferential sloped surface is located closer to the second end of the generally cylindrical body than the plurality of fuel nozzles.

12. The integral forward casing of claim 8, wherein the circumferential sloped surface is flat, such that the circumferential sloped surface is generally conical.

13. The integral forward casing of claim 8, wherein the circumferential sloped surface is concave shaped.