Ceramic matrix composite vane structures for a gas turbine engine turbine

• US 8,905,711 B2
• Filed: 05/26/2011
• Issued: 12/09/2014
• Est. Priority Date: 05/26/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Suciu, Gabriel L., Alvanos, Ioannis, Merry, Brian D., Dye, Christopher M.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): SEHN, MICHAEL L
• Application Number:
  US13/116,053
• Publication Number:
  US 20120301285A1
• Time in Patent Office: 1,293 Days
• Field of Search: 415/209.4, 415/210.1, 415/193, 415/209.3
• US Class Current: 415/193
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]

Abstract

A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.

Claims

1. A vane structure for a gas turbine engine comprising:

a CMC outer ring;

a CMC inner ring, each of said CMC outer ring and said CMC inner ring is a full, uninterrupted hoop, and each of said CMC outer ring and said CMC inner ring are uninterrupted with respect to vane pass-through apertures;

a multiple of CMC airfoil sections integrated between said CMC outer ring and said CMC inner ring; and

a splined interface extending from an outer surface of said CMC outer ring, said splined interface is axially centered relative to said multiple of CMC airfoil sections.

2. The vane structure as recited in claim 1, wherein said multiple of CMC airfoil sections are within a low-pressure turbine.

3. The vane structure as recited in claim 1, wherein said multiple of CMC airfoil sections are within a high-pressure compressor.

4. The vane structure as recited in claim 1, wherein said splined interface includes open slots.

5. The vane structure as recited in claim 1, further comprising an abradable material mounted to said CMC inner ring.

6. The vane structure as recited in claim 1, further comprising a low pressure turbine case, said CMC outer ring mounted to said low pressure turbine case through said splined interface.

7. The vane structure as recited in claim 6, wherein said low pressure turbine case is manufactured of CMC.

8. The vane structure as recited in claim 6, further comprising a support structure which extends radially inward from said low pressure turbine case.

9. The vane structure as recited in claim 8, wherein said support structure axially traps said splined interface therebetween.

10. The vane structure as recited in claim 9, wherein said support structure includes paired radial flanges.

11. The vane structure as recited in claim 1, further comprising an abradable material mounted to said CMC inner ring.

12. The vane structure as recited in claim 1, wherein said CMC outer ring and said CMC inner ring are each annularly wrapped such that there is a CMC material fiber strength in a full hoop configuration.