WE CLAIM:
1. A shroud (206) and shroud hanger assembly (200) for a gas turbine
engine, said assembly comprising:
a shroud hanger assembly (200) formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly (200) having a forward hanger portion (202) and a separate aftward hanger portion (204); and
a shroud (206) formed of a second material having a second coefficient of thermal expansion, said forward hanger portion (202) and said aftward hanger portion (204) configured to couple together to clamp across a forward radially extending wall of said shroud (206).
2. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said forward hanger portion (202) and said aftward hanger portion (204) are configured to couple together using a mechanical fastener (236) connection.
3. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said forward hanger portion (202) and said aftward hanger portion (204) are configured to couple together using a bolted (236) connection.
4. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion.
5. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein the first and second materials are ceramic matrix composite materials.
6. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said shroud (206) is supported radially by a pin (246) extending

thorough radially outwardly extending walls (208, 240) of said shroud (206) and extending through radially inwardly extending legs (210, 212) of said aftward hanger portion (204).
7. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said shroud hanger assembly (200) includes an axial web member (216) extending axially between a forward radially extending leg (210) and an aftward radially extending leg (212) of said aftward hanger portion (204).
8. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said shroud hanger assembly (200) includes a diagonal web member (218) that extends from a radially inner end (220) of a forward radially extending leg (210) to a radially outer end (222) of an aftward radially extending leg (212) of said aftward hanger portion (204).
9. The shroud (206) and shroud hanger assembly (200) as claimed in claim 1, wherein said aftward hanger portion (204) is supported radially by a first tab (224) extending axially from a radially outer end of a forward leg (210) of said aftward hanger portion (204) and a second tab (226) extending axially from a radially outer end of an aftward leg (212) of said aftward hanger portion (204), said first and said second tabs (224, 226) configured to engage circumferential lips (228, 230) of a casing (232) surrounding said shroud (206) and shroud hanger assembly (200).
10. A gas turbine engine (120) comprising:
a shroud hanger assembly (200) formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly (200) having a forward hanger portion (202) and a separate aftward hanger portion (204); and
a shroud (206) formed of a second material having a second coefficient of thermal expansion, said forward hanger portion (202) and said aftward hanger portion

(204) configured to couple together to clamp across a forward radially extending wall (208) of said shroud (206).