Gas turbine engine mid-turbine frame configuration

Patent metadata

Field	Value
Publication number	US-9920641-B2
Application number	US-201514629090-A
Country	US
Kind code	B2
Filing date	Feb 23, 2015
Priority date	Feb 23, 2015
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a core flow path extending axially about an engine axis;
a turbine section that is arranged in the core flow path, the turbine section includes a high pressure turbine and a low pressure turbine that is arranged downstream from the high pressure turbine;
a mid-turbine frame arranged in the core flow path between the high and low pressure turbines, the mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path, the vanes and inner and outer flow path surfaces provided by a unitary, one-piece cast structure, the inner flow path surface provides inlet and exit inner diameters relative to the engine axis, and the outer flow path surface provides inlet and exit outer diameters relative to the engine axis, the inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter; and
a ratio of the exit outer diameter to the axial length greater than 3.0 to 1.

2. The gas turbine engine according to claim 1 , comprising a mid-turbine frame module that includes inner and outer cases, the mid-turbine frame arranged radially between the inner and outer cases, tie rods extending through the vanes and secured to the inner and outer cases, the mid-turbine frame configured to float relative to the inner and outer cases.

3. The gas turbine engine according to claim 2 , comprising a bearing compartment mounted to the inner case.

4. The gas turbine engine according to claim 2 , wherein the outer case supports multiple circumferentially spaced centering pins that engage corresponding bosses on the mid-turbine frame, the mid-turbine frame configured to float relative centering pins.

5. The gas turbine engine according to claim 2 , wherein the mid-turbine frame includes an outer platform that provides the outer flow path surface, first and second seals mounted on the outer platform opposite the outer flow path surface and engaging the outer case.

6. The gas turbine engine according to claim 2 , wherein the mid-turbine frame includes an inner platform that provides the inner flow path surface, third and fourth seals mounted on the inner platform opposite the inner flow path surface and engaging the inner case.

7. The gas turbine engine according to claim 1 , wherein the ratio is 3.0-4.5 to 1.

8. The gas turbine engine according to claim 7 , wherein the ratio is 3.5-4.0 to 1.

9. The gas turbine engine according to claim 8 , wherein the ratio is 3.6-3.9 to 1.

10. The gas turbine engine according to claim 1 , wherein the inner flow path surface and the engine axis are at an angle of 20°-35°.

11. A mid-turbine frame module comprising:
inner and outer cases arranged about an engine axis;
a mid-turbine frame arranged radially between the inner and outer cases, the mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of a core flow path, the vanes and inner and outer flow path surfaces provided by a unitary, one-piece cast structure;
tie rods extending through the vanes and secured to the inner and outer cases, the mid-turbine frame configured to float relative to the inner and outer cases about an engine axis;
multiple circumferentially spaced centering pins supported by the outer case and that engage corresponding bosses on the mid-turbine frame, the mid-turbine frame configured to float relative centering pins; and
the inner flow path surface provides inlet and exit inner diameters relative to the engine axis, and the outer flow path surface provides inlet and exit outer diameters relative to the engine axis, the inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter, a ratio of the exit outer diameter to the axial length greater than 3.0 to 1.

12. The mid-turbine frame module according to claim 11 , wherein the ratio is 3.0-4.5 to 1.

13. The mid-turbine frame module according to claim 12 , wherein the ratio is 3.5-4.0 to 1.

14. The mid-turbine frame module according to claim 13 , wherein the ratio is 3.6-3.9 to 1.

15. The mid-turbine frame module according to claim 11 , wherein the inner flow path surface and the engine axis are at an angle of 20°-35°.

16. A mid-turbine frame comprising:
a mid-turbine frame arranged about an engine axis, the mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of a core flow path, the vanes and inner and outer flow path surfaces provided by a unitary, one-piece cast structure; and
the inner flow path surface provides inlet and exit inner diameters relative to the engine axis, and the outer flow path surface provides inlet and exit outer diameters relative to the engine axis, the inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter, a ratio of the exit outer diameter to the axial length greater than 3.0 to 1.

17. The mid-turbine frame according to claim 16 , wherein the ratio is 3.0-4.5 to 1.

18. The mid-turbine frame according to claim 17 , wherein the ratio is 3.5-4.0 to 1.

19. The mid-turbine frame according to claim 18 , wherein the ratio is 3.6-3.9 to 1.

20. The mid-turbine frame according to claim 16 , wherein the inner flow path surface and the engine axis are at an angle of 20°-35°.

Assignees

• United Technologies Corp

Inventors

• Farah Jorge I
• Ols John T

Classifications

• F05D2220/3213

  an intermediate stage of the turbine · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F05D2230/21

  by casting · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title