---
title: What is the Optimum Blade Loading in Centrifugal Compressors?
description: In this webinar, we demonstrate how compressor designers can exploit their knowledge of aerodynamics to directly address specific flow phenomena in compressors.
image: https://blog.adtechnology.com/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/Blog_banner%20Optimum%20Blade%20Loading%20in%20Compressors%20Webinar.png
---

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# What is the Optimum Blade Loading in Centrifugal Compressors?

By [Geet Nautiyal](https://blog.adtechnology.com/author/geet-nautiyal)

[3D Inverse Design](https://blog.adtechnology.com/topic/3d-inverse-design) [Compressors](https://blog.adtechnology.com/topic/compressors) February 14, 2023

Centrifugal compressors are one of the most commonly used gas compression systems across a variety of industries. For a centrifugal compressor, the impeller and diffuser are the two most critical components in achieving high-stage performance and good flow range.

Therefore, they establish the “baseline” efficiency of the compressor, so the ability to design these components with high efficiency is very important.

Over the years ADT has been involved in thousands of compressor designs across all different specific speeds and applications and has developed considerable fluid dynamic knowledge to design high-performance compressors systematically. Here is a summary of some of the main adverse fluid phenomena that cause drops in performances in these critical compressor components.

 

**Compressor Design Process**

The first step in the design of any compressor is to identify the required specific speed regime of the compressor. This will dictate the meridional shape and the pump's general flow direction. For example, a low specific speed compressor is likely to be a radial or centrifugal type. In contrast, a high specific speed compressor is likely to be of mixed flow or axial type. From the required specific speed, we can identify the main flow phenomena and loss mechanisms dominant in that particular range (see figure below). For example, leakage and secondary flow effects are more dominant in lower ranges, whereas profile/shock losses and corner separation in diffusers take priority in the higher ranges.

 

![optimum blade loading in compressors_compressor design process](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_compressor%20design%20process.webp?width=500&name=optimum%20blade%20loading%20in%20compressors_compressor%20design%20process.webp)

 

From the information above we can use design tools and 3D CFD to investigate our compressor designs; what follows are a set of principal design guidelines based on the fluid dynamics considerations of reducing dominant flow losses for a given impeller / diffuser.

 

 

### Reduction of Secondary Flow in Industrial Radial Impellers

#### **The Issue**

For medium-specific speed centrifugal compressors, secondary flows in the impeller are well acknowledged to drive the high-loss fluids in the viscous layer toward the shroud/suction surface corner region. The secondary flow phenomena have important detrimental effects on the efficiency and stability of the impeller. In addition to this, it has a dominating influence on the generation of the exit flow non-uniformity (so-called “jet-wake” flow pattern) and affects the performance and stability of the downstream diffuser.

 

![optimum blade loading in compressors_ secondary flows in centrifugal compressors](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_%20secondary%20flows%20in%20centrifugal%20compressors.webp?width=250&name=optimum%20blade%20loading%20in%20compressors_%20secondary%20flows%20in%20centrifugal%20compressors.webp)

 

#### **The Solution**

An [appropriate choice of blade loading](https://blog.adtechnology.com/optimum-blade-loading-secondary-flow-reduction-in-subsonic-impellers)<https://blog.adtechnology.com/optimum-blade-loading-secondary-flow-reduction-in-subsonic-impellers> can help reduce the pressure jump in the aft part of the blade at the shroud and increase it in the forepart, and vice versa for the hub, which helps to reduce ΔCp that is driving the secondary flow. Reducing these gradients of reduced static pressure makes it possible to eliminate secondary flows on the suction surface, resulting in a much more uniform exit flow from the impeller.

 

![optimum blade loading in compressors_ no secondary flows in centrifugal compressors](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_%20no%20secondary%20flows%20in%20centrifugal%20compressors.webp?width=260&name=optimum%20blade%20loading%20in%20compressors_%20no%20secondary%20flows%20in%20centrifugal%20compressors.webp)

 

[![Publication on Suppression of Secondary Flows](https://no-cache.hubspot.com/cta/default/2115715/23bdc805-e8a8-4410-b10f-83db4ba952ff.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/23bdc805-e8a8-4410-b10f-83db4ba952ff)

[![Publication on Centrifugal Compressor Impeller with Splitter](https://no-cache.hubspot.com/cta/default/2115715/e68edf5c-e046-4419-9b4a-2795ea0f6734.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/e68edf5c-e046-4419-9b4a-2795ea0f6734)

 

---

 

### Shock Control in Transonic Centrifugal Compressors

 

#### **The issue**

**For high-specific speed centrifugal compressors, shocks are the dominant source of loss, and there is also a complex interaction with the tip clearance vortex. So the type of loading that needs to be specified has to control the shock losses.**

 

**![optimum blade loading in compressors_shocks in centrifugal compressors](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_shocks%20in%20centrifugal%20compressors.webp?width=250&name=optimum%20blade%20loading%20in%20compressors_shocks%20in%20centrifugal%20compressors.webp)**

 

#### **The Solution**

The optimum blade loading will reduce the pressure jump across the inducer and as a result, will [reduce the strength of the shock](https://blog.adtechnology.com/shock-control-in-transonic-centrifugal-compressors) as well as the tip clearance vortex, and therefore a weaker interaction between the two.

 

![optimum blade loading in compressors_ reduce the pressure jump in centrifugal compressors](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_%20reduce%20the%20pressure%20jump%20in%20centrifugal%20compressors.webp?width=250&name=optimum%20blade%20loading%20in%20compressors_%20reduce%20the%20pressure%20jump%20in%20centrifugal%20compressors.webp)

 

[![Publication on Shock Control in Turbocharger Compressor](https://no-cache.hubspot.com/cta/default/2115715/eb41df21-018a-4ead-ac05-13b09570df27.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/eb41df21-018a-4ead-ac05-13b09570df27)

[![Publication on SRV2 Centrifugal Compressor](https://no-cache.hubspot.com/cta/default/2115715/69cd5679-6d3b-49b4-9ffa-16a3b3e6727c.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/69cd5679-6d3b-49b4-9ffa-16a3b3e6727c)

 

 

---

 

### Corner Separation Control in Vaned Diffusers

 

#### **The Issue**

**For high work coefficient centrifugal compressors, corner separation in vaned diffusers happens when the low momentum fluid at the hub suction surface corner hits the strong positive pressure gradient. **So, the optimization of blade shape is extremely important to avoid this large-scale flow separation along the hub suction surface corner.

 

**![optimum blade loading in compressors_ corner separation in vaned diffusers ](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_%20corner%20separation%20in%20vaned%20diffusers%20.webp?width=250&name=optimum%20blade%20loading%20in%20compressors_%20corner%20separation%20in%20vaned%20diffusers%20.webp)**

 

 

#### **The Solution**

The [optimum blade loading](https://blog.adtechnology.com/corner-separation-control-vaned-diffusers) diffuses the flow rapidly and reduces the strong pressure gradient. At the shroud, it results in strong secondary flows on the suction surface moving low-momentum fluids from the shroud to the hub and then to the middle of the passage. So, there is no accumulation of low momentum fluid at the endwall, and thus the corner separation can be totally suppressed.

 

![optimum blade loading in compressors_ reduces the strong pressure graident](https://blog.adtechnology.com/hs-fs/hubfs/ADT%20Blog/Optimum%20Blade%20Loading%20in%20Centrifugal%20Compressors/optimum%20blade%20loading%20in%20compressors_%20reduces%20the%20strong%20pressure%20graident.webp?width=240&name=optimum%20blade%20loading%20in%20compressors_%20reduces%20the%20strong%20pressure%20graident.webp)

 

[![Publication on Centrifugal Compressor with Vaned Diffuser](https://no-cache.hubspot.com/cta/default/2115715/578c60c8-ca9a-42e3-8037-900b92cff4fa.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/578c60c8-ca9a-42e3-8037-900b92cff4fa)

 

---

### Webinar on Optimum Blade Loading in Centrifugal Compressors

 

In this webinar, we demonstrate how compressor designers can exploit their knowledge of aerodynamics to directly address specific flow phenomena in compressors using the inverse design approach. This approach leads to a natural expansion of the explored design space as the designer is pushed to operate outside his comfort zone.

 

- **Learn** how to use the knowledge of flow physics gained from CFD and experiments to arrive at the optimum blade loading for compressors,
- **Discover **the optimum blade loading for controlling a particular flow phenomenon in compressor impellers (e.g. secondary flow and shock control),
- **Understand **how to target critical sources of loss mechanisms for your particular compressor and thus enhance its performance.

[![Playback the Webinar](https://no-cache.hubspot.com/cta/default/2115715/8873ab7c-f7c3-4019-b124-479296696992.png)](https://cta-redirect.hubspot.com/cta/redirect/2115715/8873ab7c-f7c3-4019-b124-479296696992)

 

 

### Book a LIVE demo on the design of a turbomachinery application of your choice.

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### Geet Nautiyal

Geet Nautiyal is a Turbomachinery Application Engineer at Advanced Design Technology, focusing on design, marketing and customer support aspects.

[View All Articles](https://blog.adtechnology.com/author/geet-nautiyal)

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