US 12,410,745 B2
Turbine engine with centrifugal compressor having impeller backplate offtake
Mark E. Whitlock, Zionsville, IN (US); Nathanael Cooper, Avon, IN (US); Steven Mazur, Indianapolis, IN (US); Michael Nesteroff, Indianapolis, IN (US); and Paul Melevage, Crawfordsville, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Jul. 21, 2023, as Appl. No. 18/225,089.
Application 18/225,089 is a continuation of application No. 17/747,960, filed on May 18, 2022, granted, now 11,746,695.
Application 17/747,960 is a continuation of application No. 16/824,171, filed on Mar. 19, 2020, granted, now 11,525,393, issued on Dec. 13, 2022.
Prior Publication US 2023/0374936 A1, Nov. 23, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 3/08 (2006.01); F01D 5/08 (2006.01); F02C 6/08 (2006.01); F02C 7/18 (2006.01); F02C 7/28 (2006.01)
CPC F02C 3/08 (2013.01) [F02C 6/08 (2013.01); F02C 7/18 (2013.01); F02C 7/28 (2013.01); F01D 5/081 (2013.01); F05D 2220/3219 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a centrifugal compressor including
(i) an impeller mounted for rotation about an axis and having an impeller disk and impeller blades that extend from a forward side of the impeller disk and
(ii) an impeller backing plate arranged along an aft side of the impeller disk to define a back cavity of the centrifugal compressor between the aft side of the impeller disk and the impeller backing plate,
the impeller backing plate formed to include a number of bleed holes arranged radially inwardly from an outlet tip of each of the impeller blades to allow a first portion of compressed gases discharged from the outlet tips of the impeller blades to move radially inward along a portion of the aft side of the impeller disk before moving through the number of bleed holes in the impeller backing plate, and
wherein a second portion of compressed gases is discharged from the centrifugal compressor as a compressor discharge air into a plenum surrounding a combustor,
the combustor fluidly coupled to receive a first portion of the compressor discharge air,
a turbine fluidly coupled to the combustor and including a rotor having a shaft mounted for rotation about the axis, a set of turbine blades coupled to the shaft for rotation therewith, and a seal formed from a first sealing element and a second sealing element, wherein a seal cavity is formed between the first sealing element and the second sealing element of the seal, and
a manifold mounted to the impeller backing plate and shaped to define a number of channels,
wherein the impeller backing plate is formed to include a plurality of impingement holes that extend through the impeller backing plate, the plurality of impingement holes opening into the plenum surrounding the combustor and opening into the seal cavity to transmit a second portion of the compressor discharge air from the plenum to the seal cavity,
wherein the first sealing element of the seal is configured to leak at least some of the second portion of the compressor discharge air to the back cavity as a first leaked air so that the first leaked air pressurizes the back cavity,
wherein the first portion of compressed gases flows between the impeller backing plate and the manifold through the number of channels.