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EP-4737690-A2 - GAS TURBINE ENGINE WITH A RETAINING ASSEMBLY OF A ROTOR BLADE WITH TABS AND RETAINING RING

EP4737690A2EP 4737690 A2EP4737690 A2EP 4737690A2EP-4737690-A2

Abstract

A component retaining assembly (65) includes a housing (62) including a circumferential slot (76). A component (64) is mated to the housing (62). The component (64) includes a first face (86) including at least two tabs (78). The at least two tabs (78) extending at outward from the first face (86) at least partially past a portion of the circumferential slot (76). A retaining ring (66) is disposed within the circumferential slot (76) and abuts the first face (86) of the component (64). The at least two tabs (78) overlap a portion of the retaining ring (66). A gas turbine engine (20) and a method are also disclosed.

Inventors

  • Chuong, Conway
  • WILSON, ROSS

Assignees

  • RTX Corporation

Dates

Publication Date
20260506
Application Date
20170831

Claims (14)

  1. A component retaining assembly (65) comprising: a housing (62) including a circumferential slot (76); a component (64) mated to the housing (62), the component (64) including a first face (86) including at least two tabs (78), the at least two tabs (78) extending outward from the first face (86) at least partially past a portion of the circumferential slot (76); and a retaining ring (66) disposed within the circumferential slot (76) and abutting the first face (86) of the component (64), wherein the at least two tabs (78) overlap a portion of the retaining ring (66).
  2. The assembly (65) as recited in claim 1, wherein the housing (62) includes a back face (68) and the component (64) includes a second face (83) spaced axially apart from the first face (86) with the second face (88) abutting the back face (68) of the housing (62).
  3. The assembly (65) as recited in claim 1 or 2, wherein the at least two tabs (78) are circumferentially spaced apart.
  4. The assembly (65) as recited in any of claims 1 to 3, wherein the retaining ring (66) is disposed within a radial space (94) between a bottom surface of the circumferential slot (76) and the at least two tabs (78).
  5. A gas turbine engine (20) comprising; a housing (62) disposed about an engine axis (A), the housing (62) including a circumferential slot (76); a component (64) mated to the housing (62), the component (64) including at least two axially extending tabs (78); and a retaining ring (66) disposed within the circumferential slot (76) for axially retaining the component (64) to the housing (62), the retaining ring (66) disposed within a radial space (94) between the circumferential slot (76) and the at least two axially extending tabs (78).
  6. The gas turbine engine (20) or assembly (65) as recited in any preceding claim, wherein the component (64) is fixed relative to the housing (62).
  7. The gas turbine engine (20) as recited in claim 5 or 6, wherein the housing (62) is rotatable about the engine axis (A).
  8. The gas turbine engine (20) or assembly (65) as recited in any preceding claim, wherein the housing (62) defines a rotor and the component (64) defines a portion of an airfoil assembly.
  9. The gas turbine engine (20) or assembly (65) as recited in any preceding claim, wherein the retaining ring (66) includes a split (96) configured to enable expansion for assembly into the circumferential slot (76).
  10. The gas turbine engine (20) or assembly (65) as recited in any preceding claim, wherein the circumferential slot (76) is disposed within an inner diameter (84) of the housing (62) and the retaining ring (66) is disposed radially outward of the at least two tabs (78).
  11. The gas turbine engine (20) or assembly (65) as recited in any of claims 1 to 9, wherein the circumferential slot (76) is disposed on an outer diameter (82) of the housing (62) and the retaining ring (66) is disposed radially inward of the at least two tabs (78).
  12. A method of axially retaining a component (64) to a housing (62) comprising: defining the housing (62) to include a circumferential slot (76); defining the component (64) to include at least two axially extending tabs (78); inserting a first end (98) of a retaining ring (66) into a radial space (94) between the circumferential slot (76) and one of the at least two axially extending tabs (78); and pushing the first end (98) within the circumferential slot (76) until a second end (100) of the retaining ring (66) enters the circumferential slot (76) and is disposed within the radial space (94).
  13. The method as recited in claim 12, including abutting a first face (86) of the component with the retaining ring (66) for holding the component (64) against a back face (68) of the housing (62).
  14. The method as recited in claim 12 or 13, including sizing the retaining ring (66) to include an inner diameter corresponding with a bottom surface of the circumferential slot (76) and a radial width less than a width of the radial space (94) between the circumferential slot (76) and the at least two axially extending tabs (78).

Description

BACKGROUND A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section. The compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines. Retaining rings are utilized throughout a gas turbine engine to axially retain mated components. Typical retaining rings include a split that enables the ring to be forced open for assembly into a circumferential slot. The retaining ring remains within the slot due to the size and material characteristics that resist expansion. However, an improper size or material selection may enable the ring to become dislodged from the circumferential slot. Dislodgement of a retaining ring may free the mated components or become free within the rotating structures of the gas turbine engine. Turbine engine manufacturers continue to seek further improvements to engine assembly and durability. SUMMARY In a featured embodiment, a component retaining assembly includes a housing including a circumferential slot. A component is mated to the housing. The component includes a first face including at least two tabs. The at least two tabs extending at outward from the first face at least partially past a portion of the circumferential slot. A retaining ring is disposed within the circumferential slot and abuts the first face of the component. The at least two tabs overlap a portion of the retaining ring. In another embodiment according to the previous embodiment, the housing includes a back face and the component includes a second face spaced axially apart from the first face with the second face abutting the back face of the housing. In another embodiment according to any of the previous embodiments, the at least two tabs are circumferentially spaced apart. In another embodiment according to any of the previous embodiments, the retaining ring is disposed within a radial space between a bottom surface of the circumferential slot and the at least two tabs. In another embodiment according to any of the previous embodiments, the circumferential slot is disposed within an inner diameter of the housing and the retaining ring is disposed radially outward of the at least two tabs. In another embodiment according to any of the previous embodiments, the circumferential slot is disposed on an outer diameter of the housing and the retaining ring is disposed radially inward of the at least two tabs. In another embodiment according to any of the previous embodiments, the retaining ring includes a split configured to enable expansion for assembly into the circumferential slot. In another embodiment according to any of the previous embodiments, the component is fixed relative to the housing. In another featured embodiment, a gas turbine engine includes a housing disposed about an engine axis. The housing includes a circumferential slot. A component is mated to the housing. The component includes at least two axially extending tabs. A retaining ring is disposed within the circumferential slot for axially retaining the component to the housing. The retaining ring is disposed within a radial space between the circumferential slot and the at least two axially extending tabs. In another embodiment according to the previous embodiment, the component is fixed relative to the housing. In another embodiment according to any of the previous embodiments, the housing is rotatable about the engine axis. In another embodiment according to any of the previous embodiments, the housing defines a rotor and the component defines a portion of an airfoil assembly. In another embodiment according to any of the previous embodiments, the retaining ring includes a split configured to enable expansion for assembly into the circumferential slot. In another embodiment according to any of the previous embodiments, the circumferential slot is disposed within an inner diameter of the housing and the retaining ring is disposed radially outward of the at least two tabs. In another embodiment according to any of the previous embodiments, the circumferential slot is disposed on an outer diameter of the housing and the retaining ring is disposed radially inward of the at least two tabs. In another featured embodiment, a method of axially retaining a component to a housing includes defining the housing to include a circumferential slot. The component is defined to include at least two axially extending tabs. A first end of a retaining ring is inserted into a radial space between the circumferential slot and one of the at least two axially extending tabs. The first end is pushed within the circumferential slot until a second end of