Sectioned engine structure for a gas turbine engine
An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.
1. A manufacturing method, comprising:
forming an engine structure preform including a first section preform and a second section preform formed integral with the first section preform, the first section preform including a diffuser and a combustor, and the second section preform comprising an engine case;
separating the first section preform from the second section preform to respectively provide a first section and a second section that is discrete from the first section; and
attaching the second section to the first section to provide an engine structure, the combustor disposed within a plenum of the engine structure, the engine case forming a peripheral boundary of the plenum, and a gas path extending sequentially through the diffuser, the plenum and the combustor.
2. The manufacturing method of claim 1 , wherein the forming comprises additive manufacturing the engine structure preform.
3. The manufacturing method of claim 1 , wherein the attaching comprises bonding the second section to the first section.
4. The manufacturing method of claim 1 , wherein the engine structure preform is formed as a monolithic body.
5. The manufacturing method of claim 1 , wherein, following the separating, the first section is configured as a first monolithic body and the second section is configured as a second monolithic body.
6. The manufacturing method of claim 1 , wherein
the diffuser includes a first wall, a second wall and a plurality of vanes; and
each of the plurality of vanes is within the gas path and extends between the first wall and the second wall.
7. The manufacturing method of claim 1 , wherein the combustor is configured as a reverse-flow combustor.
8. The manufacturing method of claim 1 , wherein
the engine structure further includes a turbine nozzle downstream of the combustor along the gas path; and
the first section further includes the turbine nozzle.
9. The manufacturing method of claim 8 , wherein the diffuser and the turbine nozzle share a common wall.
10. The manufacturing method of claim 8 , wherein
the turbine nozzle includes a first wall, a second wall and a plurality of vanes; and
each of the plurality of vanes is within the gas path and extends between the first wall and the second wall.
11. The manufacturing method of claim 1 , further comprising:
arranging a turbine rotor within a turbine case of the engine structure;
the first section further including the turbine case.
12. The manufacturing method of claim 1 , wherein
the engine structure further includes an exhaust duct forming a peripheral boundary of the gas path; and
the first section further includes the exhaust duct.
13. The manufacturing method of claim 1 , wherein the attaching comprises bonding the second section to the first section through a butt joint.
14. The manufacturing method of claim 1 , wherein the attaching comprises bonding the second section to the first section through a splice joint.
15. The manufacturing method of claim 1 , wherein
the engine case extends axially along and circumferentially about an axis, and the engine case includes a side wall and an end wall;
the side wall projects axially out from the end wall to an axial end of the engine case, and the engine case is attached to the first section at the axial end; and
the end wall projects radially in from the side wall to a radial end of the engine case, and the engine case is attached to the first section at the radial end.